Aircraft nacelles having adjustable chines

ABSTRACT

Aircraft nacelles having adjustable chines are described. An example apparatus includes a chine coupled to a nacelle. The chine is oriented along a fore-aft direction. The chine is translatable relative to the nacelle along the fore-aft direction.

FIELD OF THE DISCLOSURE

This disclosure relates generally to aircraft nacelles having chinesand, more specifically, to aircraft nacelles having adjustable chines.

BACKGROUND

On certain aircraft (e.g., commercial aircraft, transport aircraft,etc.), an engine of the aircraft is mounted in a nacelle that extendsfrom a pylon located under a wing of the aircraft. Such aircraft mayinclude any number (e.g., 2, 4, etc.) of wing-mounted nacelles. In manysuch aircraft, the leading edge of the nacelle is positioned forward ofthe leading edge of the wing. The high angle of attack lift capabilityof the wing is often limited by flow separation that occurs in thevicinity of the nacelle and the region downstream of the nacelle.

Aircraft manufacturers have addressed the above-described flowseparation phenomenon by installing various vortex-generating devicessuch as chines on the outer surface of the nacelle. The chine istypically mounted on a side of the nacelle and is sized and positionedto control the separation of the flow over the wing by generating avortex that interacts beneficially with a boundary layer of the uppersurface of the wing in order to reduce flow separation. Althougheffective in improving wing lift capacity at high angles of attack,chines as conventionally installed possess certain deficiencies whichdetract from their overall utility. For example, because conventionalchines are fixed in place on the nacelle and extend outwardly into theairflow, the chines produce unwanted aerodynamic drag that can have anadverse impact on the operating efficiency of the aircraft duringcruise, takeoff and landing. The optimal chine design for delaying stallcan be constrained due to the drag penalty just mentioned, or due to theneed to ensure acceptable airplane pitch characteristics at angles ofattack beyond stall.

More recently, aircraft manufacturers have considered implementingchines that are configured to generate a vortex at angles of attack forfavorably interacting with the boundary layer of the upper surface ofthe wing to delay stall, and which are further configured to minimize(e.g., eliminate) the aerodynamic drag that traditionally has beencaused by the chine during low angle-of-attack portions of flight, or toprovide a nose-down pitching moment at very high, post-stall angles ofattack. Known solutions have included chines that are rotatable relativeto the nacelle between a deployed position (e.g., for flight conditionswhere vortex generation is desirable) and a stowed position (e.g., forflight conditions where vortex generation is undesirable). Knownsolutions have also included introducing a vortex-impeding spoiler doorlocated forward of the chine, with the spoiler door being rotatablebetween a stowed position (e.g., for flight conditions where vortexgeneration is desirable) and a deployed position (e.g., for very highangle-of-attack flight conditions where vortex generation isundesirable).

SUMMARY

Aircraft nacelles having adjustable chines are disclosed herein. In someexamples, an apparatus is disclosed. In some disclosed examples, theapparatus comprises a chine coupled to a nacelle. In some disclosedexamples, the chine is oriented along a fore-aft direction. In somedisclosed examples, the chine is translatable relative to the nacellealong the fore-aft direction.

In some examples, a method is disclosed. In some disclosed examples, themethod comprises translating a chine coupled to a nacelle. In somedisclosed examples, the chine is oriented along a fore-aft direction. Insome disclosed examples, the chine is translatable relative to thenacelle along the fore-aft direction.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 illustrates an example aircraft in which an example nacellehaving an example adjustable chine can be implemented in accordance withthe teachings of this disclosure.

FIG. 2 is an outboard-looking side view of the aircraft of FIG. 1 takenalong section A-A of FIG. 1 .

FIG. 3 is a rearward-looking front view of the aircraft of FIGS. 1 and 2taken along section B-B of FIG. 1 .

FIG. 4 is a perspective view of an example nacelle having an examplechine positioned in a first example position.

FIG. 5 is a perspective view of the nacelle of FIG. 4 having the chineof FIG. 4 positioned in a second example position.

FIG. 6 is a perspective view of an example nacelle having an examplemulti-segment chine positioned in a first example configuration.

FIG. 7 is a perspective view of the nacelle of FIG. 6 having themulti-segment chine of FIG. 6 positioned in a second exampleconfiguration.

FIG. 8 is a perspective view of the nacelle of FIGS. 6 and 7 having themulti-segment chine of FIGS. 6 and 7 positioned in a third exampleconfiguration.

FIG. 9 is a perspective view of the nacelle of FIGS. 6-8 having themulti-segment chine of FIGS. 6-8 positioned in a fourth exampleconfiguration.

FIG. 10 is a perspective view of the nacelle of FIGS. 6-9 having themulti-segment chine of FIGS. 6-9 positioned in a fifth exampleconfiguration.

FIG. 11 is a perspective view of an example nacelle having an examplechine positioned in a first example position.

FIG. 12 is a perspective view of the nacelle of FIG. 11 having the chineof FIG. 11 positioned in a second example position.

FIG. 13 is a perspective view of the nacelle of FIGS. 11 and 12 havingthe chine of FIGS. 11 and 12 positioned in a third example position.

FIG. 14 is a perspective view of an example nacelle having an examplechine positioned in a first example position.

FIG. 15 is a perspective view of the nacelle of FIG. 14 having the chineof FIG. 14 positioned in a second example position.

FIG. 16 is a perspective view of the nacelle of FIGS. 14 and 15 havingthe chine of FIGS. 14 and 15 positioned in a third example position.

FIG. 17 is a perspective view of an example nacelle having an examplemulti-segment chine positioned in a first example configuration.

FIG. 18 is a perspective view of the nacelle of FIG. 17 having themulti-segment chine of FIG. 17 positioned in a second exampleconfiguration.

FIG. 19 is a perspective view of an example nacelle having an examplemulti-segment chine positioned in a first example configuration.

FIG. 20 is a perspective view of the nacelle of FIG. 19 having themulti-segment chine of FIG. 19 positioned in a second exampleconfiguration.

FIG. 21 is a perspective view of the nacelle of FIGS. 19 and 20 havingthe multi-segment chine of FIGS. 19 and 20 positioned in a third exampleconfiguration.

FIG. 22 is a perspective view of an example nacelle having an examplemulti-segment chine positioned in a first example configuration.

FIG. 23 is a perspective view of the nacelle of FIG. 22 having themulti-segment chine of FIG. 22 positioned in a second exampleconfiguration.

FIG. 24 is a perspective view of the nacelle of FIGS. 22 and 23 havingthe multi-segment chine of FIGS. 22 and 23 positioned in a third exampleconfiguration.

FIG. 25 is a perspective view of the nacelle of FIGS. 22-24 having themulti-segment chine of FIGS. 22-24 positioned in a fourth exampleconfiguration.

FIG. 26 is a perspective view of an example nacelle having examplechines positioned in a first example configuration.

FIG. 27 is a perspective view of the nacelle of FIG. 26 having thechines of FIG. 26 positioned in a second example configuration.

FIG. 28 is a perspective view of an example nacelle having an examplechine positioned in a first example position.

FIG. 29 is a perspective view of the nacelle of FIG. 28 having the chineof FIG. 28 rotated to a second example position.

FIG. 30 is a perspective view of the nacelle of FIGS. 28 and 29 havingthe chine of FIGS. 28 and 29 rotated to a third example position.

FIG. 31 is a perspective view of an example nacelle having an examplemulti-segment chine positioned in a first example configuration.

FIG. 32 is a perspective view of the nacelle of FIG. 31 having themulti-segment chine of FIG. 31 positioned in a second exampleconfiguration.

FIG. 33 is a perspective view of the nacelle of FIGS. 31 and 32 havingthe multi-segment chine of FIGS. 31 and 32 positioned in a third exampleconfiguration.

FIG. 34 is a block diagram of an example control system configured tocontrol the movement of an adjustable chine of a nacelle.

Certain examples are shown in the above-identified figures and describedin detail below. In describing these examples, like or identicalreference numbers are used to identify the same or similar elements. Thefigures are not necessarily to scale and certain features and certainviews of the figures may be shown exaggerated in scale or in schematicfor clarity and/or conciseness.

Descriptors “first,” “second,” “third,” etc. are used herein whenidentifying multiple elements or components which may be referred toseparately. Unless otherwise specified or understood based on theircontext of use, such descriptors are not intended to impute any meaningof priority or ordering in time but merely as labels for referring tomultiple elements or components separately for ease of understanding thedisclosed examples. In some examples, the descriptor “first” may be usedto refer to an element in the detailed description, while the sameelement may be referred to in a claim with a different descriptor suchas “second” or “third.” In such instances, it should be understood thatsuch descriptors are used merely for ease of referencing multipleelements or components.

DETAILED DESCRIPTION

Aircraft manufacturers have considered implementing chines that areattached to engine nacelles and configured to generate a vortex atangles of attack for favorably interacting with the boundary layer ofthe upper surface of the wing to delay stall, and which are furtherconfigured to minimize (e.g., eliminate) the aerodynamic drag thattraditionally has been caused by the chine during low angle-of-attackportions of flight, or to affect the airplane pitching momentcharacteristics at angles of attack above stall. Known solutions haveincluded chines that are rotatable relative to the nacelle between adeployed position (e.g., for flight conditions where vortex generationis desirable) and a stowed position (e.g., for flight conditions wherevortex generation is undesirable). Known solutions have also includedintroducing a vortex-impeding spoiler door located forward of the chine,with the spoiler door being rotatable between a stowed position (e.g.,for flight conditions where vortex generation is desirable) and adeployed position (e.g., for flight conditions where vortex generationis undesirable).

While the above-described nacelle chine implementations representconsiderable advancements to the state of the art, one shortcoming ofsuch known chine implementations is that they lack an ability toactively adjust and/or tune (e.g., granularly adjust and/or tune) theposition of the generated vortex during flight. Another shortcoming ofsuch known chine implementations is that they provide only near-binarycontrol (e.g., on or off) of the strength of the generated vortex duringflight. Unlike the known solutions and/or known chine implementationsdescribed above, aircraft nacelles having adjustable chines disclosedherein advantageously provide the ability to actively adjust and/or tune(e.g., granularly adjust and/or tune) the position and/or the strengthof a vortex generated by the chine during flight, thereby improvingnear-stall pitch control of the aircraft and increasing the maximumcoefficient of lift associated with the wings of the aircraft.

As used herein in the context of describing the position and/ororientation of a first object relative to a second object, the term“substantially parallel” encompasses the term parallel and more broadlyencompasses a meaning whereby the first object is positioned and/ororiented relative to the second object at an absolute angle of no morethan ten degrees (10°) from parallel. For example, a first axis that issubstantially parallel to a second axis is positioned and/or orientedrelative to the second axis at an absolute angle of no more than tendegrees (10°) from parallel. As another example, a planar surface of afirst chine that is substantially parallel to a planar surface of asecond chine is positioned and/or oriented relative to the planarsurface of the second chine at an absolute angle of no more than tendegrees (10°) from parallel. As another example, a planar surface of afirst segment of a multi-segment chine that is substantially parallel toa planar surface of a second segment of the multi-segment chine ispositioned and/or oriented relative to the planar surface of the secondsegment of the multi-segment chine at an absolute angle of no more thanten degrees (10°) from parallel.

As used herein in the context of describing the position and/ororientation of a first object relative to a second object, the term“substantially perpendicular” encompasses the term perpendicular andmore broadly encompasses a meaning whereby the first object ispositioned and/or oriented relative to the second object at an absoluteangle of no more than ten degrees (10°) from perpendicular. For example,a first axis that is substantially perpendicular to a second axis ispositioned and/or oriented relative to the second axis at an absoluteangle of no more than ten degrees (10°) from perpendicular.

As used herein in the context of describing the position and/ororientation of a first object relative to a second object, the term“substantially coplanar” encompasses the term coplanar and more broadlyencompasses a meaning whereby a planar surface of the first object is atleast substantially parallel (as defined above) to an opposing planarsurface of the second object, and whereby the planar surface of thefirst object can be offset from the opposing planar surface of thesecond object by a spacing (e.g., a tolerance) sufficient to enable theplanar surface of the first object to slide past at least a portion ofthe opposing planar surface of the second object without interference,the offset not to exceed three times the combined width of the first andsecond objects. For example, a first chine that is substantiallycoplanar with and/or relative to a second chine has a planar surfacethat is at least substantially parallel to an opposing planar surface ofthe second chine, and that can be offset from the opposing planarsurface of the second chine by a spacing (e.g., a tolerance) sufficientto enable the planar surface of the first chine to slide past at least aportion of the opposing planar surface of the second chine withoutinterference, the offset not to exceed three times the combined width ofthe first and second chines. As another example, a first segment of amulti-segment chine that is substantially coplanar with and/or relativeto a second segment of the multi-segment chine has a planar surface thatis at least substantially parallel to an opposing planar surface of thesecond segment of the multi-segment chine, and that can be offset fromthe opposing planar surface of the second segment of the multi-segmentchine by a spacing (e.g., a tolerance) sufficient to enable the planarsurface of the first segment of the multi-segment chine to slide past atleast a portion of the opposing planar surface of the second segment ofthe multi-segment chine without interference, the offset not to exceedthree times the combined width of the first and second segments of themulti-segment chine.

FIG. 1 illustrates an example aircraft 100 in which an example nacellehaving an example adjustable chine can be implemented in accordance withthe teachings of this disclosure. The aircraft 100 includes an examplefuselage 102, a first example wing 104, a second example wing 106, afirst example nacelle 108, a second example nacelle 110, a first examplechine 112, and a second example chine 114.

The fuselage 102 of FIG. 1 has a generally cylindrical shape thatdefines an example longitudinal axis 116 of the aircraft 100. The firstwing 104 of FIG. 1 is coupled to the fuselage 102 and swept in arearward direction of the aircraft 100. In other examples, the firstwing 104 can alternatively be swept in a forward direction, or canalternatively be implemented in a straight wing configuration. The firstwing 104 of FIG. 1 includes an example leading edge 118 and an exampletrailing edge 120. In some examples, the first wing 104 of FIG. 1includes one or more leading edge device(s) 122 (e.g., one or moreslat(s), slot(s), flap(s), etc.) mounted and/or positioned proximate theleading edge 118 of the first wing 104, and/or one or more trailing edgedevice(s) 124 (e.g., flap(s), aileron(s), spoiler(s), etc.) mountedand/or positioned proximate the trailing edge 120 of the first wing 104.The leading edge device(s) 122 and/or the trailing edge device(s) 124can be moved to various positions relative to the first wing 104 toadjust the coefficient of lift generated by the first wing 104 relativeto a local airflow.

The second wing 106 of FIG. 1 is coupled to the fuselage 102 and sweptin a rearward direction of the aircraft 100. In other examples, thesecond wing 106 can alternatively be swept in a forward direction, orcan alternatively be implemented in a straight wing configuration. Thesecond wing 106 of FIG. 1 includes an example leading edge 126 and anexample trailing edge 128. In some examples, the second wing 106 of FIG.1 includes one or more leading edge device(s) 130 (e.g., one or moreslat(s), slot(s), flap(s), etc.) mounted and/or positioned proximate theleading edge 126 of the second wing 106, and/or one or more trailingedge device(s) 132 (e.g., flap(s), aileron(s), spoiler(s), etc.) mountedand/or positioned proximate the trailing edge 128 of the second wing106. The leading edge device(s) 130 and/or the trailing edge device(s)132 can be moved to various positions relative to the second wing 106 toadjust the coefficient of lift generated by the second wing 106 relativeto a local airflow.

The first nacelle 108 of FIG. 1 is coupled to the first wing 104. Thefirst nacelle 108 of FIG. 1 includes an example central axis 134 and anexample leading edge 136. In the illustrated example of FIG. 1 , thecentral axis 134 of the first nacelle 108 is substantially parallel tothe longitudinal axis 116 of the fuselage 102, and the leading edge 136of the first nacelle 108 is substantially perpendicular to the centralaxis 134 of the first nacelle 108. In some examples, the central axis134 of the first nacelle 108 is defined by a rotational axis of anengine housed by the first nacelle 108.

The second nacelle 110 of FIG. 1 is coupled to the second wing 106. Thesecond nacelle 110 of FIG. 1 includes an example central axis 138 and anexample leading edge 140. In the illustrated example of FIG. 1 , thecentral axis 138 of the second nacelle 110 is substantially parallel tothe longitudinal axis 116 of the fuselage 102, and the leading edge 140of the second nacelle 110 is substantially perpendicular to the centralaxis 138 of the second nacelle 110. In some examples, the central axis138 of the second nacelle 110 is defined by a rotational axis of anengine housed by the second nacelle 110.

The first chine 112 of FIG. 1 has a substantially planar shape thatextends and/or is oriented along an example fore-aft direction 142. Insome examples, the fore-aft direction 142 is defined by an outer moldline of the first chine 112. In some examples, the fore-aft direction142 is substantially parallel to the central axis 134 of the firstnacelle 108, and/or substantially parallel to the longitudinal axis 116of the fuselage 102. In other examples, the orientation of the fore-aftdirection 142 can exceed the above-described substantially parallelrelationship(s) relative to the central axis 134 of the first nacelle108 and/or the longitudinal axis 116 of the fuselage 102. In theillustrated example of FIG. 1 , the first chine 112 is movably coupledto the first nacelle 108. For example, the first chine 112 can bemovably coupled to the first nacelle 108 in a manner that enablesmovement (e.g., translation and/or rotation) of the first chine 112relative to the first nacelle 108 along the fore-aft direction 142. Thefirst chine 112 can be moved in a controlled manner to any number ofpositions over a possible range of positions of the first chine 112, asfurther described below. In the illustrated example of FIG. 1 , thefirst chine 112 is coupled to the first nacelle 108 inboard of thecentral axis 134 of the first nacelle 108. In other examples, the firstchine 112 can alternatively be coupled to the first nacelle 108 outboardof the central axis 134 of the first nacelle 108. Furthermore, multiplechines can be coupled to the first nacelle 108 in any arrangement (e.g.,an arrangement whereby two or more chines are coupled inboard of thecentral axis 134, an arrangement whereby two or more chines are coupledoutboard of the central axis 134, an arrangement whereby at least onechine is coupled inboard of the central axis 134 and at least one chineis coupled outboard of the central axis 134, etc.).

The second chine 114 of FIG. 1 has a substantially planar shape thatextends and/or is oriented along an example fore-aft direction 144. Insome examples, the fore-aft direction 144 is defined by an outer moldline of the second chine 114. In some examples, the fore-aft direction144 is substantially parallel to the central axis 138 of the secondnacelle 110, and/or substantially parallel to the longitudinal axis 116of the fuselage 102. In other examples, the orientation of the fore-aftdirection 144 can exceed the above-described substantially parallelrelationship(s) relative to the central axis 138 of the second nacelle110 and/or the longitudinal axis 116 of the fuselage 102. In theillustrated example of FIG. 1 , the second chine 114 is movably coupledto the second nacelle 110. For example, the second chine 114 can bemovably coupled to the second nacelle 110 in a manner that enablesmovement (e.g., translation and/or rotation) of the second chine 114relative to the second nacelle 110 along the fore-aft direction 144. Thesecond chine 114 can be moved in a controlled manner to any number ofpositions over a possible range of positions of the second chine 114, asfurther described below. In the illustrated example of FIG. 1 , thesecond chine 114 is coupled to the second nacelle 110 inboard of thecentral axis 138 of the second nacelle 110. In other examples, thesecond chine 114 can alternatively be coupled to the second nacelle 110outboard of the central axis 138 of the second nacelle 110. Furthermore,multiple chines can be coupled to the first nacelle 108 in anyarrangement (e.g., an arrangement whereby two or more chines are coupledinboard of the central axis 134, an arrangement whereby two or morechines are coupled outboard of the central axis 134, an arrangementwhereby at least one chine is coupled inboard of the central axis 134and at least one chine is coupled outboard of the central axis 134,etc.).

The aircraft 100 of FIG. 1 further includes one or more controlsystem(s) configured to control the respective movements of the firstchine 112 and the second chine 114. The control system(s) canrespectively and/or collectively include, for example, one or moreactuation mechanism(s), one or more controller(s), one or more angle ofattack sensor(s), one or more leading edge device sensor(s), and one ormore trailing edge device sensor(s). In some examples, the controlsystem(s) can additionally or alternatively include one or more othersensor(s) for detecting one or more other parameter(s) including, forexample, aircraft attitude, altitude, airspeed, Mach number, icingconditions, etc. The actuation mechanism(s) of the control system can belocated (e.g., partially or fully located) within and/or on the firstnacelle 108 and/or the second nacelle 110 of the aircraft 100 of FIG. 1, and may include portions and/or components located within and/or onthe first wing 104, the second wing 106, and/or the fuselage 102 of theaircraft 100. The controller(s) of the control system can be locatedwithin and/or on any of the first nacelle 108, the second nacelle 110,the first wing 104, the second wing 106, and/or the fuselage 102 of theaircraft 100. The angle of attack sensor(s) of the control system can belocated within and/or on any of the first nacelle 108, the secondnacelle 110, the first wing 104, the second wing 106, and/or thefuselage 102 of the aircraft 100. The leading edge device sensor(s) ofthe control system can be located within and/or on the leading edgedevice(s) 122 of the first wing 104 and/or the leading edge device(s)130 of the second wing 106 of the aircraft 100, within and/or on thefirst wing 104 and/or the second wing 106 of the aircraft 100, and/orwithin and/or on the fuselage 102 of the aircraft 100. The trailing edgedevice sensor(s) of the control system can be located within and/or onthe trailing edge device(s) 124 of the first wing 104 and/or thetrailing edge device(s) of the second wing 106 of the aircraft 100,within and/or on the first wing 104 and/or the second wing 106 of theaircraft 100, and/or within and/or on the fuselage 102 of the aircraft100. The other sensor(s) (e.g., for detecting aircraft attitude,altitude, airspeed, Mach number, etc.) of the control system can belocated within and/or on any of the first nacelle 108, the secondnacelle 110, the first wing 104, the second wing 106, and/or thefuselage 102 of the aircraft 100.

The actuation mechanism(s) of the control system can be implemented byand/or as any type of actuation mechanism that is capable of beingconfigured to fit partially and/or fully within and/or on the firstnacelle 108 and/or the second nacelle 110 of the aircraft 100 of FIG. 1, and which is capable of being configured to move (e.g., translateand/or rotate) the first chine 112 and/or the second chine 114 of theaircraft 100 over a desired and/or specified range of positions. In someexamples, the actuation mechanism(s) can be implemented by and/or as anelectro-mechanical actuation system that includes one or more electroniccomponent(s). In other examples, the actuation mechanism(s) can beimplemented by and/or as a hydro-mechanical actuation system thatincludes one or more hydraulic component(s). In still other examples,the actuation mechanism(s) can be implemented by and/or as apneumatic-mechanical actuation system that includes one or morepneumatic component(s). The actuation mechanism(s) can include anynumber of mechanical components including, for example, any number ofmotors, valves, latches, pistons, rods, shafts, links, pulleys, chains,belts, hinges, pins, biasing elements, shape memory alloys, etc.

The controller(s) of the control system can be implemented by and/or asany type of hardware element capable of being configured to control theactuation mechanism(s) of the control system, and/or capable of beingconfigured to receive and/or process data sensed, measured and/ordetected by the angle of attack sensor(s), the leading edge devicesensor(s), the trailing edge device sensor(s), and/or any othersensor(s) used by the control system. The controller(s) can beimplemented by one or more controller(s), processor(s),microcontroller(s), microprocessor(s), and/or circuit(s).

The angle of attack sensor(s) of the control system is/are configured tosense, measure and/or detect the angle of attack of the first wing 104and/or the angle of attack of the second wing 106 of the aircraft 100 ofFIG. 1 (e.g., the angle between the chord line of the aircraft wing andthe relative direction of airflow against the aircraft wing), or theangle of attack relative to the fuselage 102 of the aircraft 100 (e.g.,the angle between the fuselage centerline and the relative direction ofairflow against the fuselage). The leading edge device sensor(s) of thecontrol system is/are configured to sense, measure and/or detect theposition(s) and/or angle(s) of the leading edge device(s) 122 of thefirst wing 104 and/or the position(s) and/or angle(s) of the leadingedge device(s) 130 of the second wing 106 of the aircraft 100 of FIG. 1(e.g., the position and/or angle of the leading edge device relative toa reference location and/or orientation of the aircraft wing). Thetrailing edge device sensor(s) of the control system is/are configuredto sense, measure and/or detect the position(s) and/or angle(s) of thetrailing edge device(s) 124 of the first wing 104 and/or the position(s)and/or angle(s) of the trailing edge device(s) 132 of the second wing106 of the aircraft 100 of FIG. 1 (e.g., the position and/or angle ofthe trailing edge device relative to a reference location and/ororientation of the aircraft wing). The other sensor(s) (e.g., fordetecting aircraft attitude, altitude, airspeed, Mach number, etc.) ofthe control system is/are configured to sense, measure and/or detect oneor more other parameter(s) including, for example, an attitude of theaircraft 100, an altitude of the aircraft 100, an airspeed of theaircraft 100, a Mach number of the aircraft 100, etc.

The first chine 112 and/or the second chine 114 can be moved (e.g.,translated and/or rotated, depending upon the implementation of thefirst chine 112 and/or the second chine 114) in a controlled manner toany number of positions over a possible range of positions of the firstchine 112 and/or the second chine 114. The controlled movement(s) (e.g.,translation(s) and/or rotation(s)) of the first chine 112 and/or thesecond chine 114 occur(s) via the actuation mechanism(s) of the controlsystem, with the actuation mechanism(s) being managed and/or controlledvia the controller(s) of the control system. The controller(s)generate(s) and/or transmit(s) one or more command(s) that cause(s) theactuation mechanism(s) to move (e.g., translate and/or rotate) the firstchine 112 and/or the second chine 114 to one or more position(s) (e.g.,a forward position, a rearward position, an upward position, a downwardposition, a stowed position, a deployed position, an upward-pitchedposition, a downward-pitched position, any number of intermediatepositions over a possible range of positions, etc.) specified by,indicated by, and/or derived from the command(s).

In some examples, the controller(s) is/are configured to generate one ormore command(s) that cause(s) the actuation mechanism(s) to move thefirst chine 112 and/or the second chine 114 to a specified position inresponse to the controller(s) determining and/or detecting that athreshold parameter associated with an angle of attack (or othersuitable aircraft attitude parameters) has been sensed, measured and/ordetected by one or more of the angle of attack sensor(s). In someexamples, the controller(s) is/are configured to generate one or morecommand(s) that cause(s) the actuation mechanism(s) to move the firstchine 112 and/or the second chine 114 to a specified position inresponse to the controller(s) determining and/or detecting that athreshold parameter associated with a position and/or an angle of one ormore of the leading edge device(s) 122 of the first wing 104 and/or aposition of one or more of the leading edge device(s) 130 of the secondwing 106 has/have been sensed, measured and/or detected by the leadingedge device sensor(s). In some examples, the controller(s) is/areconfigured to generate one or more command(s) that cause(s) theactuation mechanism(s) to move the first chine 112 and/or the secondchine 114 to a specified position in response to the controller(s)determining and/or detecting that a threshold parameter associated witha position and/or an angle of one or more of the trailing edge device(s)124 of the first wing 104 and/or a position of one or more of thetrailing edge device(s) 132 of the second wing 106 has/have been sensed,measured and/or detected by the trailing edge device sensor(s). In someexamples, the controller(s) is/are configured to generate one or morecommand(s) that cause(s) the actuation mechanism(s) to move the firstchine 112 and/or the second chine 114 to a specified position inresponse to the controller(s) determining and/or detecting that one ormore threshold parameter(s) associated with an attitude of the aircraft100, an altitude of the aircraft 100, an airspeed of the aircraft 100, aMach number of the aircraft 100, etc. has/have been sensed, measuredand/or detected by one or more of the other sensor(s).

FIG. 2 is an outboard-looking side view of the aircraft 100 of FIG. 1taken along section A-A of FIG. 1 . FIG. 3 is a rearward-looking frontview of the aircraft 100 of FIGS. 1 and 2 taken along section B-B ofFIG. 1 . As shown in FIGS. 2 and 3 , the first nacelle 108 of theaircraft 100 is coupled to the first wing 104 of the aircraft 100 via anexample pylon 202 that extends downward and forward from an underside ofthe first wing 104. The leading edge 136 of the first nacelle 108 islocated forward of the leading edge 118 of the first wing 104. The firstwing 104 has an example chord line 204. An angle of attack (u) of thefirst wing 104 is defined as the angle between the chord line 204 of thefirst wing 104 and the relative direction of an example airflow 206against the first wing 104.

In the illustrated example of FIGS. 2 and 3 , the first chine 112 isconfigured (e.g., sized, shaped, and oriented on the first nacelle 108)to generate an example vortex 208 that passes over an example uppersurface 210 of the first wing 104 to interact with the wing uppersurface flow field. The vortex 208 generated by the first chine 112 isconfigured to delay flow separation and/or stall, and thereby improvesthe maximum lift capability of the first wing 104 by interacting with anexample boundary layer 212 of the upper surface 210 of the first wing104.

The vortex 208 generated by the first chine 112 changes (e.g., changesits position and/or its strength) as the first chine 112 is moved (e.g.,translated and/or rotated) in a controlled manner relative to the firstnacelle 108 between a first position (e.g., a forward position, anupward position, a deployed position, etc.) and a second position (e.g.,a rearward position, a downward position, a stowed position, etc.). Forexample, when the first chine 112 is positioned in a first position(e.g., a forward position, an upward position, a deployed position,etc.), the first chine 112 is configured to generate a first vortex.When the first chine 112 is positioned in a second position (e.g., arearward position, a downward position, a stowed position, etc.) thatdiffers from the first position, the first chine 112 is configured togenerate a second vortex that differs from the first vortex. In someexamples, the first vortex has a first associated vortex position, andthe second vortex has a second associated vortex position that differsfrom the first associated vortex position. In some examples, the firstvortex has a first associated vortex strength, and the second vortex hasa second associated vortex strength that differs from the firstassociated vortex strength. The first chine 112 is capable of activelyadjusting and/or tuning (e.g., granularly adjusting and/or tuning) theposition and/or the strength of the vortex 208 generated by the firstchine 112 during flight, thereby improving near-stall and post-stallpitch control of the aircraft 100 and increasing the maximum coefficientof lift associated with the first wing 104 of the aircraft 100.

FIG. 4 is a perspective view of an example nacelle 400 having an examplechine 402 positioned in a first example position. FIG. 5 is aperspective view of the nacelle 400 of FIG. 4 having the chine 402 ofFIG. 4 positioned in a second example position. The nacelle 400 of FIGS.4 and 5 can be coupled to a wing of an aircraft (e.g., the first wing104 of the aircraft 100 of FIGS. 1-3 ). The chine 402 of the nacelle 400of FIGS. 4 and 5 can be controlled and/or adjusted by a control systemof an aircraft (e.g., the control system 3400 of FIG. 34 describedbelow, which may be implemented in the aircraft 100 of FIGS. 1-3 ).

The nacelle 400 of FIGS. 4 and 5 includes an example central axis 404and an example leading edge 406. The chine 402 of FIGS. 4 and 5 isoriented along an example fore-aft direction 408 relative to the nacelle400. In the illustrated example of FIGS. 4 and 5 , the fore-aftdirection 408 is defined by an outer mold line of the chine 402, asfurther described below. In some examples, the fore-aft direction 408 issubstantially parallel to the central axis 404 of the nacelle 400, withthe central axis 404 of the nacelle 400 being defined by a rotationalaxis of an engine housed by the nacelle 400. In other examples, thefore-aft direction 408 can additionally or alternatively besubstantially parallel to a longitudinal axis of a fuselage of anaircraft (e.g., the longitudinal axis 116 of the fuselage 102 of theaircraft 100 of FIGS. 1-3 ) that includes the nacelle 400. In stillother examples, the orientation of the fore-aft direction 408 can exceedthe above-described substantially parallel relationship(s) relative tothe central axis 404 of the nacelle 400 and/or the longitudinal axis ofthe fuselage of the aircraft. The nacelle 400 of FIGS. 4 and 5 furtherincludes an example slot 410 formed in and/or extending through anexample outer surface 412 of the nacelle 400. The slot 410 of thenacelle 400 includes an example front end 414 and an example rear end416 located opposite and/or rearward of the front end 414. In theillustrated example of FIGS. 4 and 5 , the slot 410 is oriented alongthe fore-aft direction 408.

The chine 402 of FIGS. 4 and 5 is coupled to the nacelle 400. Forexample, the chine 402 can include a root portion located inwardly(e.g., radially inwardly) relative to the outer surface 412 of thenacelle 400. The root portion of the chine 402 can be coupled (e.g.,operatively coupled) to an actuation mechanism located within thenacelle 400. An exposed portion of the chine 402 extends outwardly(e.g., radially outwardly) relative to the outer surface 412 of thenacelle 400 through the slot 410. In the illustrated example of FIGS. 4and 5 , the chine 402 is coupled to the nacelle 400 at a location thatis inboard relative to the central axis 404 of the nacelle 400. In otherexamples, the chine 402 can alternatively be coupled to the nacelle 400at a location that is outboard relative to the central axis 404 of thenacelle 400.

The chine 402 of FIGS. 4 and 5 includes an example leading edge 418, anexample trailing edge 420 located opposite and/or rearward of theleading edge 418 of the chine 402, and an example outer mold line 422defined by the leading edge 418 and the trailing edge 420 of the chine402. The chine 402 of FIGS. 4 and 5 has a substantially planar shape(e.g., as defined by the outer mold line 422) that extends and/or isoriented along the fore-aft direction 408. The chine 402 of FIGS. 4 and5 is movable and/or adjustable relative to the slot 410 and/or, moregenerally, relative to the nacelle 400 of FIGS. 4 and 5 along thefore-aft direction 408. More specifically, the chine 402 of FIGS. 4 and5 is translatable relative to the slot 410 and/or the nacelle 400 ofFIGS. 4 and 5 along the fore-aft direction 408.

In the illustrated example of FIGS. 4 and 5 , the chine 402 is movable(e.g., translatable) along the fore-aft direction 408 (e.g., within theslot 410 of the nacelle 400) between the first position (e.g., a forwardposition) shown in FIG. 4 and the second position (e.g., a rearwardposition) shown in FIG. 5 . When the chine 402 is positioned in thefirst position shown in FIG. 4 , the leading edge 418 of the chine 402is spaced from the leading edge 406 of the nacelle 400 by a firstdistance, and the leading edge 418 of the chine 402 is proximate (e.g.,adjacent or abutting) the front end 414 of the slot 410 of the nacelle400. When the chine 402 is positioned in the second position shown inFIG. 5 , the leading edge 418 of the chine 402 is spaced from theleading edge 406 of the nacelle 400 by a second distance greater thanthe first distance, and the trailing edge 420 of the chine 402 isproximate (e.g., adjacent or abutting) the rear end 416 of the slot 410of the nacelle 400.

The chine 402 of FIGS. 4 and 5 can be moved (e.g., translated along thefore-aft direction 408) in a controlled manner to any number ofintermediate positions between the first position shown in FIG. 4 andthe second position shown in FIG. 5 . The controlled movement (e.g.,translation) of the chine 402 occurs via an actuation mechanism and acontroller of a control system (e.g., the actuation mechanism 3404 andthe controller 3406 of the control system 3400 of FIG. 34 ), as furtherdescribed below.

The chine 402 of FIGS. 4 and 5 is configured (e.g., located on and/ororiented relative to the nacelle 400 of FIGS. 4 and 5 ) to generate avortex in response to an airflow presented at the chine 402. In someexamples, the vortex generated by the chine 402 favorably affects aboundary layer located on an upper surface of an aircraft wing to whichthe nacelle 400 of FIGS. 4 and 5 is coupled. Thus, the chine 402provides a positive aerodynamic impact in response to an airflowpresented at the chine 402. The vortex generated by the chine 402 ofFIGS. 4 and 5 changes (e.g., changes its position and/or its strength)as the chine 402 is moved (e.g., translated along the fore-aft direction408) between the first position (e.g., the forward position) shown inFIG. 4 and the second position (e.g., the rearward position) shown inFIG. 5 .

For example, when the chine 402 is positioned in the first positionshown in FIG. 4 , the chine 402 is configured to generate a firstvortex. When the chine 402 is positioned in the second position shown inFIG. 5 , the chine 402 is configured to generate a second vortex thatdiffers from the first vortex. In some examples, the first vortex has afirst associated vortex position, and the second vortex has a secondassociated vortex position that differs from the first associated vortexposition. In some examples, the first vortex has a first associatedvortex strength, and the second vortex has a second associated vortexstrength that differs from the first associated vortex strength.

FIG. 6 is a perspective view of an example nacelle 600 having an examplemulti-segment chine 602 positioned in a first example configuration.FIG. 7 is a perspective view of the nacelle 600 of FIG. 6 having themulti-segment chine 602 of FIG. 6 positioned in a second exampleconfiguration. FIG. 8 is a perspective view of the nacelle 600 of FIGS.6 and 7 having the multi-segment chine 602 of FIGS. 6 and 7 positionedin a third example configuration. FIG. 9 is a perspective view of thenacelle 600 of FIGS. 6-8 having the multi-segment chine 602 of FIGS. 6-8positioned in a fourth example configuration. FIG. 10 is a perspectiveview of the nacelle 600 of FIGS. 6-9 having the multi-segment chine 602of FIGS. 6-9 positioned in a fifth example configuration. The nacelle600 of FIGS. 6-10 can be coupled to a wing of an aircraft (e.g., thefirst wing 104 of the aircraft 100 of FIGS. 1-3 ). One or more segmentsof the multi-segment chine 602 of the nacelle 600 of FIGS. 6-10 can becontrolled and/or adjusted by a control system of an aircraft (e.g., thecontrol system 3400 of FIG. 34 described below, which may be implementedin the aircraft 100 of FIGS. 1-3 ).

The nacelle 600 of FIGS. 6-10 includes an example central axis 604 andan example leading edge 606. The segments of the multi-segment chine 602of FIGS. 6-10 are oriented along an example fore-aft direction 608relative to the nacelle 600. In the illustrated example of FIGS. 6-10 ,the fore-aft direction 608 is defined by one or more of the outer moldline(s) of the segments of the multi-segment chine 602, as furtherdescribed below. In some examples, the fore-aft direction 608 issubstantially parallel to the central axis 604 of the nacelle 600, withthe central axis 604 of the nacelle 600 being defined by a rotationalaxis of an engine housed by the nacelle 600. In other examples, thefore-aft direction 608 can additionally or alternatively besubstantially parallel to a longitudinal axis of a fuselage of anaircraft (e.g., the longitudinal axis 116 of the fuselage 102 of theaircraft 100 of FIGS. 1-3 ) that includes the nacelle 600. In stillother examples, the orientation of the fore-aft direction 608 can exceedthe above-described substantially parallel relationship(s) relative tothe central axis 604 of the nacelle 600 and/or the longitudinal axis ofthe fuselage of the aircraft. The nacelle 600 of FIGS. 6-10 furtherincludes an example slot 610 formed in and/or extending through anexample outer surface 612 of the nacelle 600. The slot 610 of thenacelle 600 includes an example front end 614 and an example rear end616 located opposite and/or rearward of the front end 614. In theillustrated example of FIGS. 6-10 , the slot 610 is oriented along thefore-aft direction 608.

The multi-segment chine 602 of FIGS. 6-10 includes an example firstsegment 618 (e.g., a leading segment), an example second segment 620(e.g., an intermediate segment) that is substantially coplanar with thefirst segment 618, and an example third segment 622 (e.g., a trailingsegment) that is substantially coplanar with the second segment 620. Thefirst segment 618, the second segment 620, and the third segment 622 arerespectively coupled to the nacelle 600. For example, the first segment618 and the second segment 620 can respectively include a root portionlocated inwardly (e.g., radially inwardly) relative to the outer surface612 of the nacelle 600. The root portions of the first segment 618 andthe second segment 620 can be coupled (e.g., operatively coupled) to oneor more actuation mechanism(s) located within the nacelle 600. Exposedportions of the first segment 618, the second segment 620, and the thirdsegment 622 extend outwardly (e.g., radially outwardly) relative to theouter surface 612 of the nacelle 600 through the slot 610. The thirdsegment 622 can be fixedly coupled to a static (e.g., non-movable)structure located within the nacelle 600.

In the illustrated example of FIGS. 6-10 , the first segment 618, thesecond segment 620, and the third segment 622 of the multi-segment chine602 are coupled to the nacelle 600 at a location that is inboardrelative to the central axis 604 of the nacelle 600. In other examples,the first segment 618, the second segment 620, and the third segment 622of the multi-segment chine 602 can alternatively be coupled to thenacelle 600 at a location that is outboard relative to the central axis604 of the nacelle 600. In the illustrated example of FIGS. 6-10 , themulti-segment chine 602 includes a total of three segments. In otherexamples, the multi-segment chine 602 can include a different number(e.g., 2, 4, 5, etc.) of segments implemented in a manner similar toand/or consistent with the three-segment implementation shown anddescribed in connection with FIGS. 6-10 . In the illustrated example ofFIGS. 6-10 , the first segment 618, the second segment 620, and thethird segment 622 are of an identical size and/or shape relative to oneanother. In other examples, one or more of the first segment 618, thesecond segment 620, and/or the third segment 622 can have a size and/orshape that differs from the size and/or shape of another one of thefirst segment 618, the second segment 620, and/or the third segment 622.

The first segment 618 of the multi-segment chine 602 FIGS. 6-10 includesan example leading edge 624, an example trailing edge 626 locatedopposite and/or rearward of the leading edge 624 of the first segment618, and an example outer mold line 628 defined by the leading edge 624and the trailing edge 626 of the first segment 618. The first segment618 of FIGS. 6-10 has a substantially planar shape (e.g., as defined bythe outer mold line 628) that extends and/or is oriented along thefore-aft direction 608. The first segment 618 of FIGS. 6-10 is movableand/or adjustable relative to the slot 610 and/or, more generally,relative to the nacelle 600 of FIGS. 6-10 along the fore-aft direction608. More specifically, the first segment 618 of FIGS. 6-10 istranslatable relative to the slot 610 and/or the nacelle 600 of FIGS.6-10 along the fore-aft direction 608.

The second segment 620 of the multi-segment chine 602 of FIGS. 6-10includes an example leading edge 802, an example trailing edge 630located opposite and/or rearward of the leading edge 802 of the secondsegment 620, and an example outer mold line 632 defined by the leadingedge 802 and the trailing edge 630 of the second segment 620. The secondsegment 620 of FIGS. 6-10 has a substantially planar shape (e.g., asdefined by the outer mold line 632) that extends and/or is orientedalong the fore-aft direction 608. In the illustrated example of FIGS.6-10 , the second segment 620 is substantially coplanar with the firstsegment 618 along the fore-aft direction 608. The second segment 620 ofFIGS. 6-10 is movable and/or adjustable relative to the slot 610 and/or,more generally, relative to the nacelle 600 of FIGS. 6-10 along thefore-aft direction 608. More specifically, the second segment 620 ofFIGS. 6-10 is translatable relative to the slot 610 and/or the nacelle600 of FIGS. 6-10 along the fore-aft direction 608.

The third segment 622 of the multi-segment chine 602 of FIGS. 6-10includes an example leading edge 1002, an example trailing edge 634located opposite and/or rearward of the leading edge 1002 of the thirdsegment 622, and an example outer mold line 636 defined by the leadingedge 1002 and the trailing edge 634 of the third segment 622. The thirdsegment 622 of FIGS. 6-10 has a substantially planar shape (e.g., asdefined by the outer mold line 636) that extends and/or is orientedalong the fore-aft direction 608. In the illustrated example of FIGS.6-10 , the third segment 622 is substantially coplanar with the secondsegment 620 and/or substantially coplanar with the first segment 618along the fore-aft direction 608. In the illustrated example of FIGS.6-10 , the third segment 622 is fixed relative to the slot 610 and/or,more generally, relative to the nacelle 600 of FIGS. 6-10 along thefore-aft direction 608. In other examples, the third segment 622 ofFIGS. 6-10 can be movable and/or adjustable relative to the slot 610and/or, more generally, relative to the nacelle 600 of FIGS. 6-10 alongthe fore-aft direction 608. For example, the third segment 622 of FIGS.6-10 can be translatable relative to the slot 610 and/or the nacelle 600of FIGS. 6-10 along the fore-aft direction 608.

The first configuration of the multi-segment chine 602 shown in FIG. 6corresponds to a forward position of the first segment 618, a forwardposition of the second segment 620, and a fixed position of the thirdsegment 622. The second configuration of the multi-segment chine 602shown in FIG. 7 corresponds to a first intermediate position of thefirst segment 618, a forward position of the second segment 620, and afixed position of the third segment 622. The third configuration of themulti-segment chine 602 shown in FIG. 8 corresponds to a secondintermediate position of the first segment 618, a forward position ofthe second segment 620, and a fixed position of the third segment 622.The fourth configuration of the multi-segment chine 602 shown in FIG. 9corresponds to a third intermediate position of the first segment 618,an intermediate position of the second segment 620, and a fixed positionof the third segment 622. The fifth configuration of the multi-segmentchine 602 shown in FIG. 10 corresponds to a rearward position of thefirst segment 618, a rearward position of the second segment 620, and afixed position of the third segment 622.

The first segment 618 of the multi-segment chine 602 of FIGS. 6-10 ismovable (e.g., translatable) along the fore-aft direction 608 (e.g.,within the slot 610 of the nacelle 600) between the first configurationof the multi-segment chine 602 (e.g., the forward position of the firstsegment 618) shown in FIG. 6 , the second configuration of themulti-segment chine 602 (e.g., the first intermediate position of thefirst segment 618) shown in FIG. 7 , the third configuration of themulti-segment chine 602 (e.g., the second intermediate position of thefirst segment 618) shown in FIG. 8 , the fourth configuration of themulti-segment chine 602 (e.g., the third intermediate position of thefirst segment 618) shown in FIG. 9 , and the fifth configuration of themulti-segment chine 602 (e.g., the rearward position of the firstsegment 618) shown in FIG. 10 .

When the first segment 618 is positioned in the first configuration ofthe multi-segment chine 602 shown in FIG. 6 , the leading edge 624 ofthe first segment 618 is spaced from the leading edge 606 of the nacelle600 by a first distance, and the leading edge 624 of the first segment618 is proximate (e.g., adjacent or abutting) the front end 614 of theslot 610 of the nacelle 600. When the first segment 618 is positioned inthe second configuration of the multi-segment chine 602 shown in FIG. 7, the leading edge 624 of the first segment 618 is spaced from theleading edge 606 of the nacelle 600 by a second distance greater thanthe first distance. When the first segment 618 is positioned in thethird configuration of the multi-segment chine 602 shown in FIG. 8 , theleading edge 624 of the first segment 618 is spaced from the leadingedge 606 of the nacelle 600 by a third distance greater than the seconddistance. When the first segment 618 is positioned in the fourthconfiguration of the multi-segment chine 602 shown in FIG. 9 , theleading edge 624 of the first segment 618 is spaced from the leadingedge 606 of the nacelle 600 by a fourth distance greater than the thirddistance. When the first segment 618 is positioned in the fifthconfiguration of the multi-segment chine 602 shown in FIG. 10 , theleading edge 624 of the first segment 618 is spaced from the leadingedge 606 of the nacelle 600 by a fifth distance greater than the fourthdistance, and the trailing edge 626 of the first segment 618 isproximate (e.g., adjacent or abutting) the rear end 616 of the slot 610of the nacelle 600.

The second segment 620 of the multi-segment chine 602 of FIGS. 6-10 ismovable (e.g., translatable) along the fore-aft direction 608 (e.g.,within the slot 610 of the nacelle 600) between the third configurationof the multi-segment chine 602 (e.g., the forward position of the secondsegment 620) shown in FIG. 8 , the fourth configuration of themulti-segment chine 602 (e.g., the intermediate position of the secondsegment 620) shown in FIG. 9 , and the fifth configuration of themulti-segment chine 602 (e.g., the rearward position of the secondsegment 620) shown in FIG. 10 .

When the second segment 620 is positioned in the third configuration ofthe multi-segment chine 602 shown in FIG. 8 , the leading edge 802 ofthe second segment 620 is spaced from the leading edge 606 of thenacelle 600 by a sixth distance (e.g., equal to the third distanceassociated with the first segment 618). When the second segment 620 ispositioned in the fourth configuration of the multi-segment chine 602shown in FIG. 9 , the leading edge 802 of the second segment 620 isspaced from the leading edge 606 of the nacelle 600 by a seventhdistance greater than the sixth distance. When the second segment 620 ispositioned in the fifth configuration of the multi-segment chine 602shown in FIG. 10 , the leading edge 802 of the second segment 620 isspaced from the leading edge 606 of the nacelle 600 by an eighthdistance (e.g., equal to the fifth distance associated with the firstsegment 618) greater than the seventh distance, and the trailing edge630 of the second segment 620 is proximate (e.g., adjacent or abutting)the rear end 616 of the slot 610 of the nacelle 600.

In the illustrated example of FIGS. 6-10 , the leading edge 624 of thefirst segment 618 of the multi-segment chine 602 is transversely alignedalong the fore-aft direction 608 with the leading edge 802 of the secondsegment 620 of the multi-segment chine 602 when the multi-segment chine602 is positioned in any of the third, fourth and/or fifthconfigurations shown in FIGS. 8-10 . More specifically, the outer moldline 628 of the first segment 618 is transversely aligned along thefore-aft direction 608 with the outer mold line 632 of the secondsegment 620 when the multi-segment chine 602 is positioned in any of thethird, fourth and/or fifth configurations shown in FIGS. 8-10 . In theillustrated example of FIGS. 6-10 , the leading edge 624 of the firstsegment 618 of the multi-segment chine 602 and/or the leading edge 802of the second segment 620 of the multi-segment chine 602 is/aretransversely aligned along the fore-aft direction 608 with the leadingedge 1002 of the third segment 622 of the multi-segment chine 602 whenthe multi-segment chine 602 is positioned in the fifth configurationshown in FIG. 10 . More specifically, the outer mold line 628 of thefirst segment 618 and/or the outer mold line 632 of the second segment620 is/are transversely aligned along the fore-aft direction 608 withthe outer mold line 636 of the third segment 622 when the multi-segmentchine 602 is positioned in the fifth configuration shown in FIG. 10 .

In the illustrated example of FIGS. 6-10 , the first segment 618 and/orthe second segment 620 of the multi-segment chine 602 can be moved(e.g., translated along the fore-aft direction 608) in a controlledmanner to any number of intermediate positions between the firstposition shown in FIG. 6 and the fifth position shown in FIG. 10 . Thecontrolled movement(s) (e.g., translation(s)) of the first segment 618and/or the second segment 620 of the multi-segment chine 602 occur(s)via one or more actuation mechanism(s) and one or more controller(s) ofa control system (e.g., the actuation mechanism 3404 and the controller3406 of the control system 3400 of FIG. 34 ), as further describedbelow.

The first segment 618, the second segment 620, and the third segment 622of the multi-segment chine 602 of FIGS. 6-10 are configured (e.g.,located on and/or oriented relative to the nacelle 600 of FIGS. 6-10 )to collectively generate a vortex in response to an airflow presented atthe multi-segment chine 602. In some examples, the vortex generated bythe first segment 618, the second segment 620, and the third segment 622of the multi-segment chine 602 favorably affects a boundary layerlocated on an upper surface of an aircraft wing to which the nacelle 600of FIGS. 6-10 is coupled. Thus, the multi-segment chine 602 provide apositive aerodynamic impact in response to an airflow presented at themulti-segment chine 602. The vortex generated by the first segment 618,the second segment 620, and the third segment 622 of the multi-segmentchine 602 of FIGS. 6-10 changes (e.g., changes its position and/or itsstrength) as one or more of the first segment 618, the second segment620, and/or the third segment 622 of the multi-segment chine 602 is/aremoved (e.g., translated along the fore-aft direction 608) between thefirst configuration shown in FIG. 6 , the second configuration shown inFIG. 7 , the third configuration shown in FIG. 8 , the fourthconfiguration shown in FIG. 9 , and the fifth configuration shown inFIG. 10 .

For example, when the multi-segment chine 602 is positioned in the firstconfiguration shown in FIG. 6 , the first segment 618, the secondsegment 620, and the third segment 622 of the multi-segment chine 602are configured to collectively generate a first vortex. When themulti-segment chine 602 is positioned in the second configuration shownin FIG. 7 , the first segment 618, the second segment 620, and the thirdsegment 622 of the multi-segment chine 602 are configured tocollectively generate a second vortex that differs from the firstvortex. When the multi-segment chine 602 is positioned in the thirdconfiguration shown in FIG. 8 , the first segment 618, the secondsegment 620, and the third segment 622 of the multi-segment chine 602are configured to collectively generate a third vortex that differs fromthe first vortex and also differs from the second vortex. When themulti-segment chine 602 is positioned in the fourth configuration shownin FIG. 9 , the first segment 618, the second segment 620, and the thirdsegment 622 of the multi-segment chine 602 are configured tocollectively generate a fourth vortex that differs from the firstvortex, differs from the second vortex, and differs from the thirdvortex. When the multi-segment chine 602 is positioned in the fifthconfiguration shown in FIG. 10 , the first segment 618, the secondsegment 620, and the third segment 622 of the multi-segment chine 602are configured to collectively generate a fifth vortex that differs fromthe first vortex, differs from the second vortex, differs from the thirdvortex, and differs from the fourth vortex. In some examples, the firstvortex has a first associated vortex position, the second vortex has asecond associated vortex position that differs from the first associatedvortex position, the third vortex has a third associated vortex positionthat differs from each of the first and second associated vortexpositions, the fourth vortex has a fourth associated vortex positionthat differs from each of the first, second, and third associated vortexpositions, and the fifth vortex has a fifth associated vortex positionthat differs from each of the first, second, third, and fourthassociated vortex positions. In some examples, the first vortex has afirst associated vortex strength, the second vortex has a secondassociated vortex strength that differs from the first associated vortexstrength, the third vortex has a third associated vortex strength thatdiffers from each of the first and second associated vortex strengths,the fourth vortex has a fourth associated vortex strength that differsfrom each of the first, second, and third associated vortex strengths,and the fifth vortex has a fifth associated vortex strength that differsfrom each of the first, second, third, and fourth associated vortexstrengths.

FIG. 11 is a perspective view of an example nacelle 1100 having anexample chine 1102 positioned in a first example position. FIG. 12 is aperspective view of the nacelle 1100 of FIG. 11 having the chine 1102 ofFIG. 11 positioned in a second example position. FIG. 13 is aperspective view of the nacelle 1100 of FIGS. 11 and 12 having the chine1102 of FIGS. 11 and 12 positioned in a third example position. Thenacelle 1100 of FIGS. 11-13 can be coupled to a wing of an aircraft(e.g., the first wing 104 of the aircraft 100 of FIGS. 1-3 ). The chine1102 of the nacelle 1100 of FIGS. 11-13 can be controlled and/oradjusted by a control system of an aircraft (e.g., the control system3400 of FIG. 34 described below, which may be implemented in theaircraft 100 of FIGS. 1-3 ).

The nacelle 1100 of FIGS. 11-13 includes an example central axis 1104and an example leading edge 1106. The chine 1102 of FIGS. 11-13 isoriented along an example fore-aft direction 1108 relative to thenacelle 1100. In the illustrated example of FIGS. 11-13 , the fore-aftdirection 1108 is defined by an outer mold line of the chine 1102, asfurther described below. In some examples, the fore-aft direction 1108is substantially parallel to the central axis 1104 of the nacelle 1100,with the central axis 1104 of the nacelle 1100 being defined by arotational axis of an engine housed by the nacelle 1100. In otherexamples, the fore-aft direction 1108 can additionally or alternativelybe substantially parallel to a longitudinal axis of a fuselage of anaircraft (e.g., the longitudinal axis 116 of the fuselage 102 of theaircraft 100 of FIGS. 1-3 ) that includes the nacelle 1100. In stillother examples, the orientation of the fore-aft direction 1108 canexceed the above-described substantially parallel relationship(s)relative to the central axis 1104 of the nacelle 1100 and/or thelongitudinal axis of the fuselage of the aircraft. The nacelle 1100 ofFIGS. 11-13 further includes an example slot 1110 formed in and/orextending through an example outer surface 1112 of the nacelle 1100. Theslot 1110 of the nacelle 1100 includes an example front end 1114 and anexample rear end 1116 located opposite and/or rearward of the front end1114. In the illustrated example of FIGS. 11-13 , the slot 1110 isoriented along the fore-aft direction 1108.

The chine 1102 of FIGS. 11-13 is coupled to the nacelle 1100. Forexample, the chine 1102 can include a root portion located inwardly(e.g., radially inwardly) relative to the outer surface 1112 of thenacelle 1100. The root portion of the chine 1102 can be coupled (e.g.,operatively coupled) to an actuation mechanism located within thenacelle 1100. An exposed portion of the chine 1102 extends outwardly(e.g., radially outwardly) relative to the outer surface 1112 of thenacelle 1100 through the slot 1110. In the illustrated example of FIGS.11-13 , the chine 1102 is coupled to the nacelle 1100 at a location thatis inboard relative to the central axis 1104 of the nacelle 1100. Inother examples, the chine 1102 can alternatively be coupled to thenacelle 1100 at a location that is outboard relative to the central axis1104 of the nacelle 1100.

The chine 1102 of FIGS. 11-13 includes an example leading edge 1118, anexample trailing edge 1120 located opposite and/or rearward of theleading edge 1118 of the chine 1102, and an example outer mold line 1122defined by the leading edge 1118 and the trailing edge 1120 of the chine1102. The chine 1102 of FIGS. 11-13 has a substantially planar shape(e.g., as defined by the outer mold line 1122) that extends and/or isoriented along the fore-aft direction 1108. The chine 1102 of FIGS.11-13 is movable and/or adjustable relative to the slot 1110 and/or,more generally, relative to the nacelle 1100 of FIGS. 11-13 along thefore-aft direction 1108. More specifically, the chine 1102 of FIGS.11-13 is translatable relative to the slot 1110 and/or the nacelle 1100of FIGS. 11-13 along the fore-aft direction 1108.

In the illustrated example of FIGS. 11-13 , the chine 1102 is movable(e.g., translatable) along the fore-aft direction 1108 (e.g., within theslot 1110 of the nacelle 1100) between the first position (e.g., aforward position) shown in FIG. 11 , the second position (e.g., anintermediate position) shown in FIG. 12 , and the third position (e.g.,a rearward position) shown in FIG. 13 . When the chine 1102 ispositioned in the first position shown in FIG. 11 , the leading edge1118 of the chine 1102 is spaced from the leading edge 1106 of thenacelle 1100 by a first distance, and the leading edge 1118 of the chine1102 is proximate (e.g., adjacent or abutting) the front end 1114 of theslot 1110 of the nacelle 1100. When the chine 1102 is positioned in thesecond position shown in FIG. 12 , the leading edge 1118 of the chine1102 is spaced from the leading edge 1106 of the nacelle 1100 by asecond distance greater than the first distance. When the chine 1102 ispositioned in the third position shown in FIG. 13 , the leading edge1118 of the chine 1102 is spaced from the leading edge 1106 of thenacelle 1100 by a third distance greater than the second distance, andthe trailing edge 1120 of the chine 1102 is proximate (e.g., adjacent orabutting) the rear end 1116 of the slot 1110 of the nacelle 1100.

In the illustrated example of FIGS. 11-13 , the first position of thechine 1102 shown in FIG. 11 corresponds to a deployed position of thechine 1102, the second position of the chine 1102 shown in FIG. 12corresponds to a partially-deployed and/or a partially-stowed positionof the chine 1102, and the third position of the chine 1102 shown inFIG. 13 corresponds to a stowed position of the chine 1102. The chine1102 becomes increasingly submerged and/or retracted relative to theslot 1110 and/or the outer surface 1112 of the nacelle 1100 as the chine1102 moves (e.g., translates) from the first position shown in FIG. 11to the third position shown in FIG. 13 . For example, when the chine1102 is positioned in the first position shown in FIG. 11 , an exampleportion 1124 of the chine 1102 is exposed and/or extends outwardly(e.g., radially outwardly) relative to the outer surface 1112 of thenacelle 1100 through the slot 1110. As the chine 1102 moves (e.g.,translates) from the first position shown in FIG. 11 to the secondposition shown in FIG. 12 , the portion 1124 of the chine 1102 becomespartially submerged and/or partially retracted relative to the outersurface 1112 of the nacelle 1100 through the slot 1110. As the chine1102 moves (e.g., translates) from the second position shown in FIG. 12to the third position shown in FIG. 13 , the portion 1124 of the chine1102 becomes fully submerged and/or fully retracted relative to theouter surface 1112 of the nacelle 1100 through the slot 1110. In someexamples, the chine 1102 is movable (e.g., translatable) to a position(e.g., a fully-rearward position) in which the outer mold line 1122 ofthe chine 1102 becomes fully submerged and/or fully retracted relativeto the outer surface 1112 of the nacelle 1100 through the slot 1110.

The chine 1102 of FIGS. 11-13 can be moved (e.g., translated along thefore-aft direction 1108) in a controlled manner to any number ofintermediate positions between the first position shown in FIG. 11 andthe third position shown in FIG. 13 . The controlled movement (e.g.,translation) of the chine 1102 occurs via an actuation mechanism and acontroller of a control system (e.g., the actuation mechanism 3404 andthe controller 3406 of the control system 3400 of FIG. 34 ), as furtherdescribed below.

The chine 1102 of FIGS. 11-13 is configured (e.g., located on and/ororiented relative to the nacelle 1100 of FIGS. 11-13 ) to generate avortex in response to an airflow presented at the chine 1102. In someexamples, the vortex generated by the chine 1102 favorably affects aboundary layer located on an upper surface of an aircraft wing to whichthe nacelle 1100 of FIGS. 11-13 is coupled. Thus, the chine 1102provides a positive aerodynamic impact in response to an airflowpresented at the chine 1102. The vortex generated by the chine 1102 ofFIGS. 11-13 changes (e.g., changes its position and/or its strength) asthe chine 1102 is moved (e.g., translated along the fore-aft direction1108) between the first position (e.g., a forward position) shown inFIG. 11 , the second position (e.g., an intermediate position) shown inFIG. 12 , and the third position (e.g., a rearward position) shown inFIG. 13 .

For example, when the chine 1102 is positioned in the first positionshown in FIG. 11 , the chine 1102 is configured to generate a firstvortex. When the chine 1102 is positioned in the second position shownin FIG. 12 , the chine 1102 is configured to generate a second vortexthat differs from the first vortex. When the chine 1102 is positioned inthe third position shown in FIG. 13 , the chine 1102 is configured togenerate a third vortex that differs from the first vortex and alsodiffers from the second vortex. In some examples, the first vortex has afirst associated vortex position, the second vortex has a secondassociated vortex position that differs from the first associated vortexposition, and the third vortex has a third associated vortex positionthat differs from the first associated vortex position and also differsfrom the second associated vortex position. In some examples, the firstvortex has a first associated vortex strength, the second vortex has asecond associated vortex strength that differs from the first associatedvortex strength, and the third vortex has a third associated vortexstrength that differs from the first associated vortex strength and alsodiffers from the second associated vortex strength.

FIG. 14 is a perspective view of an example nacelle 1400 having anexample chine 1402 positioned in a first example position. FIG. 15 is aperspective view of the nacelle 1400 of FIG. 14 having the chine 1402 ofFIG. 14 positioned in a second example position. FIG. 16 is aperspective view of the nacelle 1400 of FIGS. 14 and 15 having the chine1402 of FIGS. 14 and 15 positioned in a third example position. Thenacelle 1400 of FIGS. 14-16 can be coupled to a wing of an aircraft(e.g., the first wing 104 of the aircraft 100 of FIGS. 1-3 ). The chine1402 of the nacelle 1400 of FIGS. 14-16 can be controlled and/oradjusted by a control system of an aircraft (e.g., the control system3400 of FIG. 34 described below, which may be implemented in theaircraft 100 of FIGS. 1-3 ).

The nacelle 1400 of FIGS. 14-16 includes an example central axis 1404and an example leading edge 1406. The chine 1402 of FIGS. 14-16 isoriented along an example fore-aft direction 1408 relative to thenacelle 400. In the illustrated example of FIGS. 14-16 , the fore-aftdirection 1408 is defined by an outer mold line of the chine 1402, asfurther described below. In some examples, the fore-aft direction 1408is substantially parallel to the central axis 1404 of the nacelle 1400,with the central axis 1404 of the nacelle 1400 being defined by arotational axis of an engine housed by the nacelle 1400. In otherexamples, the fore-aft direction 1408 can additionally or alternativelybe substantially parallel to a longitudinal axis of a fuselage of anaircraft (e.g., the longitudinal axis 116 of the fuselage 102 of theaircraft 100 of FIGS. 1-3 ) that includes the nacelle 1400. In stillother examples, the orientation of the fore-aft direction 1408 canexceed the above-described substantially parallel relationship(s)relative to the central axis 1404 of the nacelle 1400 and/or thelongitudinal axis of the fuselage of the aircraft. The nacelle 1400 ofFIGS. 14-16 further includes an example slot 1410 formed in and/orextending through an example outer surface 1412 of the nacelle 1400. Theslot 1410 of the nacelle 1400 includes an example front end 1414 and anexample rear end 1416 located opposite and/or rearward of the front end1414. In the illustrated example of FIGS. 14-16 , the slot 1410 isoriented along the fore-aft direction 1408.

The chine 1402 of FIGS. 14-16 is coupled to the nacelle 1400. Forexample, the chine 1402 can include a root portion located inwardly(e.g., radially inwardly) relative to the outer surface 1412 of thenacelle 1400. The root portion of the chine 1402 can be coupled (e.g.,operatively coupled) to an actuation mechanism located within thenacelle 1400. An exposed portion of the chine 1402 extends outwardly(e.g., radially outwardly) relative to the outer surface 1412 of thenacelle 1400 through the slot 1410. In the illustrated example of FIGS.14-16 , the chine 1402 is coupled to the nacelle 1400 at a location thatis inboard relative to the central axis 1404 of the nacelle 1400. Inother examples, the chine 1402 can alternatively be coupled to thenacelle 1400 at a location that is outboard relative to the central axis1404 of the nacelle 1400.

The chine 1402 of FIGS. 14-16 includes an example leading edge 1418, anexample trailing edge 1420 located opposite and/or rearward of theleading edge 1418 of the chine 1402, and an example outer mold line 1422defined by the leading edge 1418 and the trailing edge 1420 of the chine1402. The chine 1402 of FIGS. 14-16 has a substantially planar shape(e.g., as defined by the outer mold line 1422) that extends and/or isoriented along the fore-aft direction 1408. The chine 1402 of FIGS.14-16 is movable and/or adjustable relative to the slot 1410 and/or,more generally, relative to the nacelle 1400 of FIGS. 14-16 . Morespecifically, the chine 1402 of FIGS. 14-16 is rotatable relative to theslot 1410 and/or the nacelle 1400 of FIGS. 14-16 . Rotation of the chine1402 occurs about an example axis of rotation 1426. In the illustratedexample of FIGS. 14-16 , the axis of rotation 1426 of the chine 1402 issubstantially perpendicular to a plane of the chine 1402 defined by theouter mold line 1422 of the chine 1402.

In the illustrated example of FIGS. 14-16 , the chine 1402 is movable(e.g., rotatable about the axis of rotation 1426) within the slot 1410of the nacelle 1400 between the first position (e.g., an upwardposition) shown in FIG. 14 , the second position (e.g., an intermediateposition) shown in FIG. 15 , and the third position (e.g., a downwardposition) shown in FIG. 16 . The second position of the chine 1402 shownin FIG. 15 is angularly displaced from the first position of the chine1402 shown in FIG. 14 , and the third position of the chine 1402 shownin FIG. 16 is angularly displaced from the second position of the chine1402 shown in FIG. 15 . The first position of the chine 1402 shown inFIG. 14 corresponds to a deployed position of the chine 1402, the secondposition of the chine 1402 shown in FIG. 15 corresponds to apartially-deployed and/or a partially-stowed position of the chine 1402,and the third position of the chine 1402 shown in FIG. 16 corresponds toa stowed position of the chine 1402. The chine 1402 becomes increasinglysubmerged and/or retracted relative to the slot 1410 and/or the outersurface 1412 of the nacelle 1400 as the chine 1402 moves (e.g., rotates)from the first position shown in FIG. 14 to the third position shown inFIG. 16 .

For example, when the chine 1402 is positioned in the first positionshown in FIG. 14 , an example portion 1424 of the chine 1402 is exposedand/or extends outwardly (e.g., radially outwardly) relative to theouter surface 1412 of the nacelle 1400 through the slot 1410. As thechine 1402 moves (e.g., rotates) from the first position shown in FIG.14 to the second position shown in FIG. 15 , the portion 1424 of thechine 1402 becomes partially submerged and/or partially retractedrelative to the outer surface 1412 of the nacelle 1400 through the slot1410. As the chine 1402 moves (e.g., rotates) from the second positionshown in FIG. 15 to the third position shown in FIG. 16 , the portion1424 of the chine 1402 becomes fully submerged and/or fully retractedrelative to the outer surface 1412 of the nacelle 1400 through the slot1410. In some examples, the chine 1402 is movable (e.g., rotatable) to aposition (e.g., a fully-downward position) in which the outer mold line1422 of the chine 1402 becomes fully submerged and/or fully retractedrelative to the outer surface 1412 of the nacelle 1400 through the slot1410.

The chine 1402 of FIGS. 14-16 can be moved (e.g., rotated about the axisof rotation 1426) in a controlled manner to any number of intermediatepositions between the first position shown in FIG. 14 and the thirdposition shown in FIG. 16 . The controlled movement (e.g., rotation) ofthe chine 1402 occurs via an actuation mechanism and a controller of acontrol system (e.g., the actuation mechanism 3404 and the controller3406 of the control system 3400 of FIG. 34 ), as further describedbelow.

The chine 1402 of FIGS. 14-16 is configured (e.g., located on and/ororiented relative to the nacelle 1400 of FIGS. 14-16 ) to generate avortex in response to an airflow presented at the chine 1402. In someexamples, the vortex generated by the chine 1402 favorably affects aboundary layer located on an upper surface of an aircraft wing to whichthe nacelle 1400 of FIGS. 14-16 is coupled. Thus, the chine 1402provides a positive aerodynamic impact in response to an airflowpresented at the chine 1402. The vortex generated by the chine 1402 ofFIGS. 14-16 changes (e.g., changes its position and/or its strength) asthe chine 1402 is moved (e.g., rotated about the axis of rotation 1426)between the first position (e.g., an upward position) shown in FIG. 14 ,the second position (e.g., an intermediate position) shown in FIG. 15 ,and the third position (e.g., a downward position) shown in FIG. 16 .

For example, when the chine 1402 is positioned in the first positionshown in FIG. 14 , the chine 1402 is configured to generate a firstvortex. When the chine 1402 is positioned in the second position shownin FIG. 15 , the chine 1402 is configured to generate a second vortexthat differs from the first vortex. When the chine 1402 is positioned inthe third position shown in FIG. 16 , the chine 1402 is configured togenerate a third vortex that differs from the first vortex and alsodiffers from the second vortex. In some examples, the first vortex has afirst associated vortex position, the second vortex has a secondassociated vortex position that differs from the first associated vortexposition, and the third vortex has a third associated vortex positionthat differs from the first associated vortex position and also differsfrom the second associated vortex position. In some examples, the firstvortex has a first associated vortex strength, the second vortex has asecond associated vortex strength that differs from the first associatedvortex strength, and the third vortex has a third associated vortexstrength that differs from the first associated vortex strength and alsodiffers from the second associated vortex strength.

FIG. 17 is a perspective view of an example nacelle 1700 having anexample multi-segment chine 1702 positioned in a first exampleconfiguration. FIG. 18 is a perspective view of the nacelle 1700 of FIG.17 having the multi-segment chine 1702 of FIG. 17 positioned in a secondexample configuration. The nacelle 1700 of FIGS. 17 and 18 can becoupled to a wing of an aircraft (e.g., the first wing 104 of theaircraft 100 of FIGS. 1-3 ). A segment (e.g., a forward and/or leadingsegment) of the multi-segment chine 1702 of the nacelle 1700 of FIGS. 17and 18 can be controlled and/or adjusted by a control system of anaircraft (e.g., the control system 3400 of FIG. 34 described below,which may be implemented in the aircraft 100 of FIGS. 1-3 ).

The nacelle 1700 of FIGS. 17 and 18 includes an example central axis1704 and an example leading edge 1706. The multi-segment chine 1702 ofFIGS. 17 and 18 is oriented along an example fore-aft direction 1708relative to the nacelle 1700. In the illustrated example of FIGS. 17 and18 , the fore-aft direction 1708 is defined by an outer mold line of themulti-segment chine 1702, as further described below. In some examples,the fore-aft direction 1708 is substantially parallel to the centralaxis 1704 of the nacelle 1700, with the central axis 1704 of the nacelle1700 being defined by a rotational axis of an engine housed by thenacelle 1700. In other examples, the fore-aft direction 1708 canadditionally or alternatively be substantially parallel to alongitudinal axis of a fuselage of an aircraft (e.g., the longitudinalaxis 116 of the fuselage 102 of the aircraft 100 of FIGS. 1-3 ) thatincludes the nacelle 1700. In still other examples, the orientation ofthe fore-aft direction 1708 can exceed the above-described substantiallyparallel relationship(s) relative to the central axis 1704 of thenacelle 1700 and/or the longitudinal axis of the fuselage of theaircraft. The nacelle 1700 of FIGS. 17 and 18 further includes anexample slot 1710 formed in and/or extending through an example outersurface 1712 of the nacelle 1700. The slot 1710 of the nacelle 1700includes an example front end 1714 and an example rear end 1716 locatedopposite and/or rearward of the front end 1714. In the illustratedexample of FIGS. 17 and 18 , the slot 1710 is oriented along thefore-aft direction 1708.

The multi-segment chine 1702 of FIGS. 17 and 18 includes an examplefirst segment 1718 (e.g., a leading segment) and an example secondsegment 1720 (e.g., a trailing segment) that is substantially coplanarwith the first segment 1718. The first segment 1718 and the secondsegment 1720 are respectively coupled to the nacelle 1700. For example,the first segment 1718 of the multi-segment chine 1702 can include aroot portion located inwardly (e.g., radially inwardly) relative to theouter surface 1712 of the nacelle 1700. The root portion of the firstsegment 1718 of the multi-segment chine 1702 can be coupled (e.g.,operatively coupled) to an actuation mechanism located within thenacelle 1700. An exposed portion of the first segment 1718 of themulti-segment chine 1702 extends outwardly (e.g., radially outwardly)relative to the outer surface 1712 of the nacelle 1700 through the slot1710. The second segment 1720 of the multi-segment chine 1702 can befixedly coupled to a static (e.g., non-movable) structure located onand/or within the nacelle 1700. In the illustrated example of FIGS. 17and 18 , the multi-segment chine 1702 is coupled to the nacelle 1700 ata location that is inboard relative to the central axis 1704 of thenacelle 1700. In other examples, the multi-segment chine 1702 canalternatively be coupled to the nacelle 1700 at a location that isoutboard relative to the central axis 1704 of the nacelle 1700.

The first segment 1718 of the multi-segment chine 1702 of FIGS. 17 and18 includes an example leading edge 1722, an example trailing edge 1724located opposite and/or rearward of the leading edge 1722 of the firstsegment 1718, and an example outer mold line 1726 defined by the leadingedge 1722 and the trailing edge 1724 of the first segment 1718. Thefirst segment 1718 of the multi-segment chine 1702 of FIGS. 17 and 18has a substantially planar shape (e.g., as defined by the outer moldline 1726) that extends and/or is oriented along the fore-aft direction1708. The first segment 1718 of the multi-segment chine 1702 of FIGS. 17and 18 is movable and/or adjustable relative to the slot 1710 and/or,more generally, relative to the nacelle 1700 of FIGS. 17 and 18 alongthe fore-aft direction 1708. More specifically, the first segment 1718of the multi-segment chine 1702 of FIGS. 17 and 18 is rotatable relativeto the slot 1710 and/or the nacelle 1700 of FIGS. 17 and 18 . Rotationof the first segment 1718 of the multi-segment chine 1702 occurs aboutan example axis of rotation 1732. In the illustrated example of FIGS. 17and 18 , the axis of rotation 1732 of the first segment 1718 of themulti-segment chine 1702 is substantially perpendicular to a plane ofthe first segment 1718 defined by the outer mold line 1726 of the firstsegment 1718.

The second segment 1720 of the multi-segment chine 1702 of FIGS. 17 and18 includes an example leading edge 1802, an example trailing edge 1728located opposite and/or rearward of the leading edge 1802 of the secondsegment 1720, and an example outer mold line 1730 defined by the leadingedge 1802 and the trailing edge 1728 of the second segment 1720. Thesecond segment 1720 of the multi-segment chine 1702 of FIGS. 17 and 18has a substantially planar shape (e.g., as defined by the outer moldline 1730) that extends and/or is oriented along the fore-aft direction1708. In the illustrated example of FIGS. 17 and 18 , the second segment1720 of the multi-segment chine 1702 is substantially coplanar withfirst segment 1718 of the multi-segment chine 1702 along the fore-aftdirection 1708. In the illustrated example of FIGS. 17 and 18 , theleading edge 1802 of the second segment 1720 of the multi-segment chine1702 has a curved shape that is complementary to a curved shape of thetrailing edge 1724 of the first segment 1718 of the multi-segment chine1702. In other examples, the leading edge 1802 of the second segment1720 of the multi-segment chine 1702 can alternatively have a shape thatis not complementary to a shape of the trailing edge 1724 of the firstsegment 1718 of the multi-segment chine 1702. The second segment 1720 ofthe multi-segment chine 1702 of FIGS. 17 and 18 is fixed relative to theslot 1710 and/or, more generally, relative to the nacelle 1700 of FIGS.17 and 18 along the fore-aft direction 1708. Thus, the first segment1718 of the multi-segment chine 1702 is movable (e.g., rotatable)relative to the second segment 1720 of the multi-segment chine 1702.

In the illustrated example of FIGS. 17 and 18 , the first segment 1718of the multi-segment chine 1702 is movable (e.g., rotatable about theaxis of rotation 1732) within the slot 1710 of the nacelle 1700 betweenthe first position (e.g., an upward position) shown in FIG. 17 and thesecond position (e.g., a downward position) shown in FIG. 18 . Thesecond position of the first segment 1718 of the multi-segment chine1702 shown in FIG. 18 is angularly displaced from the first position ofthe first segment 1718 of the multi-segment chine 1702 shown in FIG. 17. In the illustrated example of FIGS. 17 and 18 , the first position ofthe first segment 1718 of the multi-segment chine 1702 shown in FIG. 17corresponds to a deployed position of the first segment 1718, and thesecond position of the first segment 1718 of the multi-segment chine1702 shown in FIG. 18 corresponds to a stowed position of the firstsegment 1718. The first segment 1718 of the multi-segment chine 1702becomes increasingly submerged and/or retracted relative to the slot1710 and/or the outer surface 1712 of the nacelle 1700 as the firstsegment 1718 moves (e.g., rotates) from the first position shown in FIG.17 to the second position shown in FIG. 18 .

For example, when the first segment 1718 of the multi-segment chine 1702is positioned in the first position shown in FIG. 17 , an exampleportion 1734 of the first segment 1718 of the multi-segment chine 1702is exposed and/or extends outwardly (e.g., radially outwardly) relativeto the outer surface 1712 of the nacelle 1700 through the slot 1710. Asthe first segment 1718 of the multi-segment chine 1702 moves (e.g.,rotates) from the first position shown in FIG. 17 to the second positionshown in FIG. 18 , the portion 1734 of the first segment 1718 of themulti-segment chine 1702 becomes fully submerged and/or fully retractedrelative to the outer surface 1712 of the nacelle 1700 through the slot1710. In some examples, the first segment 1718 of the multi-segmentchine 1702 is movable (e.g., rotatable) to a position (e.g., afully-downward position) in which the outer mold line 1726 of the firstsegment 1718 of the multi-segment chine 1702 becomes fully submergedand/or fully retracted relative to the outer surface 1712 of the nacelle1700 through the slot 1710.

The first segment 1718 of the multi-segment chine 1702 of FIGS. 17 and18 can be moved (e.g., rotated about the axis of rotation 1732) in acontrolled manner to any number of intermediate positions between thefirst position shown in FIG. 17 and the second position shown in FIG. 18. The controlled movement (e.g., rotation) of the first segment 1718 ofthe multi-segment chine 1702 occurs via an actuation mechanism and acontroller of a control system (e.g., the actuation mechanism 3404 andthe controller 3406 of the control system 3400 of FIG. 34 ), as furtherdescribed below.

The multi-segment chine 1702 of FIGS. 17 and 18 is configured (e.g.,located on and/or oriented relative to the nacelle 1700 of FIGS. 17 and18 ) to generate a vortex in response to an airflow presented at themulti-segment chine 1702. In some examples, the vortex generated by themulti-segment chine 1702 favorably affects a boundary layer located onan upper surface of an aircraft wing to which the nacelle 1700 of FIGS.17 and 18 is coupled. Thus, the multi-segment chine 1702 provides apositive aerodynamic impact in response to an airflow presented at themulti-segment chine 1702. The vortex generated by the multi-segmentchine 1702 of FIGS. 17 and 18 changes (e.g., changes its position and/orits strength) as the first segment 1718 of the multi-segment chine 1702is moved (e.g., rotated about the axis of rotation 1732) between thefirst position (e.g., an upward position) shown in FIG. 17 and thesecond position (e.g., a downward position) shown in FIG. 18 .

For example, when the first segment 1718 of the multi-segment chine 1702is positioned in the first position shown in FIG. 17 , the multi-segmentchine 1702 is configured to generate a first vortex. When the firstsegment 1718 of the multi-segment chine 1702 is positioned in the secondposition shown in FIG. 18 , the multi-segment chine 1702 is configuredto generate a second vortex that differs from the first vortex. In someexamples, the first vortex has a first associated vortex position, andthe second vortex has a second associated vortex position that differsfrom the first associated vortex position. In some examples, the firstvortex has a first associated vortex strength, and the second vortex hasa second associated vortex strength that differs from the firstassociated vortex strength.

As described above in connection with FIGS. 17 and 18 , the first (e.g.,leading) segment 1718 of the multi-segment chine 1702 is rotatable, andthe second (e.g., trailing) segment 1720 of the multi-segment chine 1702is fixed. In other examples, the first (e.g., leading) segment 1718 ofthe multi-segment chine 1702 can alternatively be fixed, and the second(e.g., trailing) segment 1720 of the multi-segment chine 1702 canalternatively be rotatable. Furthermore, the respective sizes and/ordimensions (e.g., lengths) of the first segment 1718 and the secondsegment 1720 of the multi-segment chine 1702 may differ relative to theconfiguration shown in FIGS. 17 and 18 . For example, the first (e.g.,leading) segment 1718 of the multi-segment chine 1702 can have a lengththat exceeds a length of the second (e.g., trailing) segment 1720 of themulti-segment chine 1702.

FIG. 19 is a perspective view of an example nacelle 1900 having anexample multi-segment chine 1902 positioned in a first exampleconfiguration. FIG. 20 is a perspective view of the nacelle 1900 of FIG.19 having the multi-segment chine 1902 of FIG. 19 positioned in a secondexample configuration. FIG. 21 is a perspective view of the nacelle 1900of FIGS. 19 and 20 having the multi-segment chine 1902 of FIGS. 19 and20 positioned in a third example configuration. The nacelle 1900 ofFIGS. 19-21 can be coupled to a wing of an aircraft (e.g., the firstwing 104 of the aircraft 100 of FIGS. 1-3 ). The multi-segment chine1902 of the nacelle 1900 of FIGS. 19-21 can be controlled and/oradjusted by a control system of an aircraft (e.g., the control system3400 of FIG. 34 described below, which may be implemented in theaircraft 100 of FIGS. 1-3 ).

The nacelle 1900 of FIGS. 19-21 includes an example central axis 1904and an example leading edge 1906. The multi-segment chine 1902 of FIGS.19-21 is oriented along an example fore-aft direction 1908 relative tothe nacelle 1900. In the illustrated example of FIGS. 19-21 , thefore-aft direction 1908 is defined by an outer mold line of themulti-segment chine 1902, as further described below. In some examples,the fore-aft direction 1908 is substantially parallel to the centralaxis 1904 of the nacelle 1900, with the central axis 1904 of the nacelle1900 being defined by a rotational axis of an engine housed by thenacelle 1900. In other examples, the fore-aft direction 1908 canadditionally or alternatively be substantially parallel to alongitudinal axis of a fuselage of an aircraft (e.g., the longitudinalaxis 116 of the fuselage 102 of the aircraft 100 of FIGS. 1-3 ) thatincludes the nacelle 1900. In still other examples, the orientation ofthe fore-aft direction 1908 can exceed the above-described substantiallyparallel relationship(s) relative to the central axis 1904 of thenacelle 1900 and/or the longitudinal axis of the fuselage of theaircraft. In the illustrated example of FIGS. 19-21 , the nacelle 1900further includes an example slot 1910 formed in and/or extending throughan example outer surface 1912 of the nacelle 1900. The slot 1910 of thenacelle 1900 includes an example front end 1914 and an example rear end1916 located opposite and/or rearward of the front end 1914. In theillustrated example of FIGS. 19-21 , the slot 1910 is oriented along thefore-aft direction 1908. In other examples, the slot 1910 of FIGS. 19-21can be omitted from the nacelle 1900.

The multi-segment chine 1902 of FIGS. 19-21 includes an example firstsegment 1918 and an example second segment 1920 that is substantiallycoplanar with the first segment 1918 of the multi-segment chine 1902.The first segment 1918 and the second segment 1920 of the multi-segmentchine 1902 are respectively coupled to the nacelle 1900. For example,the first segment 1918 of the multi-segment chine 1902 can respectivelyinclude a root portion located inwardly (e.g., radially inwardly)relative to the outer surface 1912 of the nacelle 1900. The root portionof the first segment 1918 can be coupled (e.g., operatively coupled) toan actuation mechanism located within the nacelle 1900. An exposedportion of the first segment 1918 extends outwardly (e.g., radiallyoutwardly) relative to the outer surface 1912 of the nacelle 1900through the slot 1910. The second segment 1920 of the multi-segmentchine 1902 can be fixedly coupled to a static (e.g., non-movable)structure located on and/or within the nacelle 1900. In the illustratedexample of FIGS. 19-21 , the multi-segment chine 1902 (including thefirst segment 1918 and the second segment 1920 thereof) is coupled tothe nacelle 1900 at a location that is inboard relative to the centralaxis 1904 of the nacelle 1900. In other examples, the multi-segmentchine 1902 can alternatively be coupled to the nacelle 1900 at alocation that is outboard relative to the central axis 1904 of thenacelle 1900.

The first segment 1918 of the multi-segment chine 1902 of FIGS. 19-21includes an example leading edge 1922, an example trailing edge 1924located opposite and/or rearward of the leading edge 1922 of the firstsegment 1918, an example outer mold line 1926 defined by the leadingedge 1922 and the trailing edge 1924 of the first segment 1918, and oneor more example airflow opening(s) 1928 (e.g., one or more throughhole(s)) extending transversely through the first segment 1918 of themulti-segment chine 1902. The first segment 1918 of the multi-segmentchine 1902 of FIGS. 19-21 has a substantially planar shape (e.g., asdefined by the outer mold line 1926) that extends and/or is orientedalong the fore-aft direction 1908. The first segment 1918 of themulti-segment chine 1902 of FIGS. 19-21 is movable and/or adjustablerelative to the nacelle 1900 of FIGS. 19-21 along the fore-aft direction1908. More specifically, the first segment 1918 of the multi-segmentchine 1902 of FIGS. 19-21 is translatable relative to the nacelle 1900of FIGS. 19-21 along the fore-aft direction 1908.

The second segment 1920 of the multi-segment chine 1902 of FIGS. 19-21includes an example leading edge 1930, an example trailing edge 1932located opposite and/or rearward of the leading edge 1930 of the secondsegment 1920, an example outer mold line 1934 defined by the leadingedge 1930 and the trailing edge 1932 of the second segment 1920, and oneor more example airflow opening(s) 2002 (e.g., one or more throughhole(s)) extending transversely through the second segment 1920 of themulti-segment chine 1902. The second segment 1920 of the multi-segmentchine 1902 of FIGS. 19-21 has a substantially planar shape (e.g., asdefined by the outer mold line 1934 that extends and/or is orientedalong the fore-aft direction 1908. In the illustrated example of FIGS.19-21 , the second segment 1920 of the multi-segment chine 1902 issubstantially coplanar with the first segment 1918 of the multi-segmentchine 1902 along the fore-aft direction 1908. In some examples, thesecond segment 1920 of the multi-segment chine 1902 can be formed as aframe that substantially houses and/or surrounds the exposed portion ofthe first segment 1918 that extends outwardly (e.g., radially outwardly)relative to the outer surface 1912 of the nacelle 1900 through the slot1910.

In the illustrated example of FIGS. 19-21 , the second segment 1920 ofthe multi-segment chine 1902 is fixed relative to the nacelle 1900 ofFIGS. 19-21 along the fore-aft direction 1908. Thus, the first segment1918 of the multi-segment chine 1902 is movable (e.g., translatable)relative to the second segment 1920 of the multi-segment chine 1902. Inother examples, the second segment 1920 of the multi-segment chine 1902of FIGS. 19-21 can be movable and/or adjustable relative to the nacelle1900 of FIGS. 19-21 along the fore-aft direction 1908. For example, thesecond segment 1920 of the multi-segment chine 1902 of FIGS. 19-21 canbe translatable relative to the nacelle 1900 of FIGS. 19-21 along thefore-aft direction 1908 of the nacelle 1900. In such examples, the firstsegment 1918 of the multi-segment chine 1902 remains movable (e.g.,translatable) relative to the second segment 1920 of the multi-segmentchine 1902.

Respective ones of the airflow opening(s) 1928 of the first segment 1918of the multi-segment chine 1902 are sized, shaped and/or configured tobe selectively transversely aligned (e.g., transversely misaligned,partially transversely aligned and/or fully transversely aligned) withcorresponding respective ones of the airflow opening(s) 2002 of thesecond segment 1920 of the multi-segment chine 1902 along the fore-aftdirection 1908. In the illustrated example of FIGS. 19-21 , respectiveones of the airflow opening(s) 1928 of the first segment andcorresponding respective ones of the airflow opening(s) 2002 of thesecond segment 1920 have generally rectangular shapes that extend in afirst direction. In other examples, respective ones of the airflowopening(s) 1928 of the first segment and/or corresponding respectiveones of the airflow opening(s) 2002 of the second segment 1920 canalternatively have generally rectangular shapes that extend in a seconddirection differing from the first direction shown in FIGS. 19-21 . Instill other examples, respective ones of the airflow opening(s) 1928 ofthe first segment and/or corresponding respective ones of the airflowopening(s) 2002 of the second segment 1920 can alternatively havenon-rectangular shapes (e.g., triangular shapes, circular shapes, ovularshapes, irregular shapes, etc.) differing from the rectangular shapesshown in FIGS. 19-21 . The airflow opening(s) 1928 of the first segment1918 and/or the airflow opening(s) 2002 of the second segment 1920 canbe of any quantity and/or number, can be of any size and/or shape, andcan be arranged and/or oriented according to any regular or irregularpattern and/or configuration that enables respective ones of the airflowopening(s) 1928 of the first segment 1918 to be selectively transverselyaligned (e.g., transversely misaligned, partially transversely alignedand/or fully transversely aligned) with corresponding respective ones ofthe airflow opening(s) 2002 of the second segment 1920 along thefore-aft direction 1908.

The first configuration of the multi-segment chine 1902 shown in FIG. 19corresponds to a forward position of the first segment 1918 of themulti-segment chine 1902 and a fixed position of the second segment 1920of the multi-segment chine 1902. The second configuration of themulti-segment chine 1902 shown in FIG. 20 corresponds to an intermediateposition of the first segment 1918 of the multi-segment chine 1902 and afixed position of the second segment 1920 of the multi-segment chine1902. The third configuration of the multi-segment chine 1902 shown inFIG. 21 corresponds to a rearward position of the first segment 1918 ofthe multi-segment chine 1902 and a fixed position of the second segment1920 of the multi-segment chine 1902. The first segment 1918 of themulti-segment chine 1902 of FIGS. 19-21 is movable (e.g., translatable)along the fore-aft direction 1908 (e.g., within the slot 1910 of thenacelle 1900) between the first configuration of the multi-segment chine1902 (e.g., the forward position of the first segment 1918) shown inFIG. 19 , the second configuration of the multi-segment chine 1902(e.g., the intermediate position of the first segment 1918) shown inFIG. 20 , and the third configuration of the multi-segment chine 1902(e.g., the rearward position of the first segment 1918) shown in FIG. 21.

When the first segment 1918 of the multi-segment chine 1902 ispositioned in the first configuration of the multi-segment chine 1902shown in FIG. 19 , the leading edge 1922 of the first segment 1918 isspaced from the leading edge 1906 of the nacelle 1900 by a firstdistance. When the first segment 1918 of the multi-segment chine 1902 ispositioned in the second configuration of the multi-segment chine 1902shown in FIG. 20 , the leading edge 1922 of the first segment 1918 isspaced from the leading edge 1906 of the nacelle 1900 by a seconddistance greater than the first distance. When the first segment 1918 ofthe multi-segment chine 1902 is positioned in the third configuration ofthe multi-segment chine 1902 shown in FIG. 21 , the leading edge 1922 ofthe first segment 1918 is spaced from the leading edge 1906 of thenacelle 1900 by a third distance greater than the second distance.

When the first segment 1918 of the multi-segment chine 1902 ispositioned (e.g., relative to the second segment 1920 of themulti-segment chine 1902) in the first configuration shown in FIG. 19 ,the first segment 1918 covers the airflow opening(s) 2002 of the secondsegment 1920, and the second segment 1920 covers the airflow opening(s)1928 of the first segment 1918. In other words, respective ones of theairflow opening(s) 1928 of the first segment 1918 are not transverselyaligned with corresponding respective ones of the airflow opening(s)2002 of the second segment 1920 along the fore-aft direction 1908. Thus,air is unable to flow transversely through the multi-segment chine 1902of FIGS. 19-21 when the multi-segment chine 1902 is positioned in thefirst configuration shown in FIG. 19 .

When the first segment 1918 of the multi-segment chine 1902 ispositioned (e.g., relative to the second segment 1920 of themulti-segment chine 1902) in the second configuration shown in FIG. 20 ,the first segment 1918 only partially covers the airflow opening(s) 2002of the second segment 1920, and the second segment 1920 only partiallycovers the airflow opening(s) 1928 of the first segment 1918. In otherwords, respective ones of the airflow opening(s) 1928 of the firstsegment 1918 are partially transversely aligned with correspondingrespective ones of the airflow opening(s) 2002 of the second segment1920 along the fore-aft direction 1908. Thus, a first volume of air isable to flow transversely through the multi-segment chine 1902 of FIGS.19-21 when the multi-segment chine 1902 is positioned in the secondconfiguration shown in FIG. 20 .

When the first segment 1918 of the multi-segment chine 1902 ispositioned (e.g., relative to the second segment 1920 of themulti-segment chine 1902) in the third configuration shown in FIG. 21 ,the first segment 1918 does not cover the airflow opening(s) 2002 of thesecond segment 1920, and the second segment 1920 does not cover theairflow opening(s) 1928 of the first segment 1918. In other words,respective ones of the airflow opening(s) 1928 of the first segment 1918are transversely aligned with corresponding respective ones of theairflow opening(s) 2002 of the second segment 1920 along the fore-aftdirection 1908. Thus, a second volume of air greater than the firstvolume of air is able to flow transversely through the multi-segmentchine 1902 of FIGS. 19-21 when the multi-segment chine 1902 ispositioned in the third configuration shown in FIG. 21 .

In the illustrated example of FIGS. 19-21 , the first segment 1918 ofthe multi-segment chine 1902 can be moved (e.g., translated along thefore-aft direction 1908) in a controlled manner to any number ofintermediate positions between the first position shown in FIG. 19 andthe third position shown in FIG. 21 . The controlled movement (e.g.,translation) of the first segment 1918 of the multi-segment chine 1902occurs via an actuation mechanism and a controller of a control system(e.g., the actuation mechanism 3404 and the controller 3406 of thecontrol system 3400 of FIG. 34 ), as further described below.

The multi-segment chine 1902 of FIGS. 19-21 is configured (e.g., locatedon and/or oriented relative to the nacelle 1900 of FIGS. 19-21 ) togenerate a vortex in response to an airflow presented at themulti-segment chine 1902. In some examples, the vortex generated by themulti-segment chine 1902 favorably affects a boundary layer located onan upper surface of an aircraft wing to which the nacelle 1900 of FIGS.19-21 is coupled. Thus, the multi-segment chine 1902 provides a positiveaerodynamic impact in response to an airflow presented at themulti-segment chine 1902. The vortex generated by the multi-segmentchine 1902 of FIGS. 19-21 changes (e.g., changes its position and/or itsstrength) as the first segment 1918 of the multi-segment chine 1902 ismoved (e.g., translated along the fore-aft direction 1908) between thefirst position (e.g., a forward position of the first segment 1918)shown in FIG. 19 , the second position (e.g., an intermediate positionof the first segment 1918) shown in FIG. 20 , and the third position(e.g., a rearward position of the first segment 1918) shown in FIG. 21 .

For example, when the first segment 1918 of the multi-segment chine 1902is positioned in the first position shown in FIG. 19 , the multi-segmentchine 1902 is configured to generate a first vortex. When the firstsegment 1918 of the multi-segment chine 1902 is positioned in the secondposition shown in FIG. 20 , the multi-segment chine 1902 is configuredto generate a second vortex that differs from the first vortex. When thefirst segment 1918 of the multi-segment chine 1902 is positioned in thethird position shown in FIG. 21 , the multi-segment chine 1902 isconfigured to generate a third vortex that differs from the first vortexand also differs from the second vortex. In some examples, the firstvortex has a first associated vortex position, the second vortex has asecond associated vortex position that differs from the first associatedvortex position, and the third vortex has a third associated vortexposition that differs from the first associated vortex position and alsodiffers from the second associated vortex position. In some examples,the first vortex has a first associated vortex strength, the secondvortex has a second associated vortex strength that differs from thefirst associated vortex strength, and the third vortex has a thirdassociated vortex strength that differs from the first associated vortexstrength and also differs from the second associated vortex strength.

FIG. 22 is a perspective view of an example nacelle 2200 having anexample multi-segment chine 2202 positioned in a first exampleconfiguration. FIG. 23 is a perspective view of the nacelle 2200 of FIG.22 having the multi-segment chine 2202 of FIG. 22 positioned in a secondexample configuration. FIG. 24 is a perspective view of the nacelle 2200of FIGS. 22 and 23 having the multi-segment chine 2202 of FIGS. 22 and23 positioned in a third example configuration. FIG. 25 is a perspectiveview of the nacelle 2200 of FIGS. 22-24 having the multi-segment chine2202 of FIGS. 22-24 positioned in a fourth example configuration. Thenacelle 2200 of FIGS. 22-25 can be coupled to a wing of an aircraft(e.g., the first wing 104 of the aircraft 100 of FIGS. 1-3 ). Themulti-segment chine 2202 of the nacelle 2200 of FIGS. 22-25 can becontrolled and/or adjusted by a control system of an aircraft (e.g., thecontrol system 3400 of FIG. 34 described below, which may be implementedin the aircraft 100 of FIGS. 1-3 ).

The nacelle 2200 of FIGS. 22-25 includes an example central axis 2204and an example leading edge 2206. The multi-segment chine 2202 of FIGS.22-25 is rotatably coupled to the nacelle 2200, and is rotatablerelative to the nacelle 2200 about an example axis of rotation 2208. Insome examples, the axis of rotation 2208 of the multi-segment chine 2202is substantially parallel to the central axis 2204 of the nacelle 2200,with the central axis 2204 of the nacelle 2200 being defined by arotational axis of an engine housed by the nacelle 2200. In otherexamples, the axis of rotation 2208 of the multi-segment chine 2202 canbe oriented at an angle beyond substantially parallel relative to thecentral axis 2204 of the nacelle 2200. The nacelle 2200 of FIGS. 22-25further includes an example recess 2210 formed in and/or extending intoan example outer surface 2212 of the nacelle 2200. The recess 2210 issized, shaped and/or configured to receive the multi-segment chine 2202of FIGS. 22-25 and/or respective segments thereof, as further describedbelow.

The multi-segment chine 2202 of FIGS. 22-25 includes an example firstsegment 2214 (e.g., a leading segment), an example second segment 2216(e.g., an intermediate segment), and an example third segment 2218(e.g., a trailing segment). The first segment 2214, the second segment2216, and the third segment 2218 are respectively rotatably coupled tothe nacelle 2200, and are independently rotatable relative to thenacelle 2200 about the axis of rotation 2208. For example, the firstsegment 2214 of the multi-segment chine 2202 is rotatable about the axisof rotation 2208 independently of any rotation of the second segment2216 and/or the third segment 2218 of the multi-segment chine 2202 aboutthe axis of rotation 2208, the second segment 2216 of the multi-segmentchine 2202 is rotatable about the axis of rotation 2208 independently ofany rotation of the first segment 2214 and/or the third segment 2218 ofthe multi-segment chine 2202 about the axis of rotation 2208, and thethird segment 2218 of the multi-segment chine 2202 is rotatable aboutthe axis of rotation 2208 independently of any rotation of the firstsegment 2214 and/or the second segment 2216 of the multi-segment chine2202 about the axis of rotation 2208.

In the illustrated example of FIGS. 22-25 , the multi-segment chine 2202is coupled to the nacelle 2200 at a location that is inboard relative tothe central axis 2204 of the nacelle 2200. In other examples, themulti-segment chine 2202 can alternatively be coupled to the nacelle2200 at a location that is outboard relative to the central axis 2204 ofthe nacelle 2200. In the illustrated example of FIGS. 22-25 , themulti-segment chine 2202 includes a total of three segments. In otherexamples, the multi-segment chine 2202 can include a different number(e.g., 2, 4, 5, etc.) of segments implemented in a manner similar toand/or consistent with the three-segment implementation shown anddescribed in connection with FIGS. 22-25 .

The first segment 2214 of the multi-segment chine 2202 of FIGS. 22-25includes an example leading edge 2220, an example trailing edge 2222located opposite and/or rearward of the leading edge 2220 of the firstsegment 2214, and an outer mold line 2224 defined by the leading edge2220 and the trailing edge 2222 of the first segment 2214. The firstsegment 2214 of the multi-segment chine 2202 has a substantially planarshape (e.g., as defined by the outer mold line 2224). In some examples,the substantially planar shape of the first segment 2214 can becontoured to match a contour of the recess 2210 and/or a contour of alocal area of the outer surface 2212 of the nacelle 2200.

The second segment 2216 of the multi-segment chine 2202 of FIGS. 22-25includes an example leading edge 2226, an example trailing edge 2228located opposite and/or rearward of the leading edge 2226 of the secondsegment 2216, and an outer mold line 2230 defined by the leading edge2226 and the trailing edge 2228 of the second segment 2216. The leadingedge 2226 of the second segment 2216 of the multi-segment chine 2202 hasa curved shape that is complementary to a curved shape of the trailingedge 2222 of the first segment 2214 of the multi-segment chine 2202. Thesecond segment 2216 of the multi-segment chine 2202 has a substantiallyplanar shape (e.g., as defined by the outer mold line 2230). In someexamples, the substantially planar shape of the second segment 2216 canbe contoured to match a contour of the recess 2210 and/or a contour of alocal area of the outer surface 2212 of the nacelle 2200.

The third segment 2218 of the multi-segment chine 2202 of FIGS. 22-25includes an example leading edge 2232, an example trailing edge 2234located opposite and/or rearward of the leading edge 2232 of the thirdsegment 2218, and an outer mold line 2236 defined by the leading edge2232 and the trailing edge 2234 of the third segment 2218. The leadingedge 2232 of the third segment 2218 of the multi-segment chine 2202 hasa curved shape that is complementary to a curved shape of the trailingedge 2228 of the second segment 2216 of the multi-segment chine 2202.The third segment 2218 of the multi-segment chine 2202 has asubstantially planar shape (e.g., as defined by the outer mold line2236). In some examples, the substantially planar shape of the thirdsegment 2218 can be contoured to match a contour of the recess 2210and/or a contour of a local area of the outer surface 2212 of thenacelle 2200.

The first configuration of the multi-segment chine 2202 shown in FIG. 22corresponds to a deployed position of the first segment 2214, a deployedposition of the second segment 2216, and a deployed position of thethird segment 2218. The second configuration of the multi-segment chine2202 shown in FIG. 23 corresponds to a stowed position of the firstsegment 2214, a deployed position of the second segment 2216, and adeployed position of the third segment 2218. The third configuration ofthe multi-segment chine 2202 shown in FIG. 24 corresponds to a stowedposition of the first segment 2214, a stowed position of the secondsegment 2216, and a deployed position of the third segment 2218. Thefourth configuration of the multi-segment chine 2202 shown in FIG. 25corresponds to a stowed position of the first segment 2214, a stowedposition of the second segment 2216, and a stowed position of the thirdsegment 2218.

The first segment 2214 of the multi-segment chine 2202 of FIGS. 22-25 isrotatable about the axis of rotation 2208 between the deployed positionof the first segment 2214 shown in FIG. 22 and the stowed position ofthe first segment 2214 shown in FIGS. 23-25 . The outer mold line 2224of the first segment 2214 extends along the outer surface 2212 of thenacelle 2200 when the first segment 2214 is positioned in its stowedposition. As shown in FIGS. 23-25 , the outer mold line 2224 of thefirst segment 2214 is received in the recess 2210 of the nacelle 2200when the first segment 2214 is positioned in its stowed position. Theouter mold line 2224 of the first segment 2214 extends outwardly (e.g.,radially outwardly) from the outer surface 2212 of the nacelle 2200 whenthe first segment 2214 is positioned in its deployed position.

The second segment 2216 of the multi-segment chine 2202 of FIGS. 22-25is rotatable about the axis of rotation 2208 between the deployedposition of the second segment 2216 shown in FIGS. 22 and 23 and thestowed position of the second segment 2216 shown in FIGS. 24 and 25 .The outer mold line 2230 of the second segment 2216 extends along theouter surface 2212 of the nacelle 2200 when the second segment 2216 ispositioned in its stowed position. As shown in FIGS. 24 and 25 , theouter mold line 2230 of the second segment 2216 is received in therecess 2210 of the nacelle 2200 when the second segment 2216 ispositioned in its stowed position. The outer mold line 2230 of thesecond segment 2216 extends outwardly (e.g., radially outwardly) fromthe outer surface 2212 of the nacelle 2200 when the second segment 2216is positioned in its deployed position.

The third segment 2218 of the multi-segment chine 2202 of FIGS. 22-25 isrotatable about the axis of rotation 2208 between the deployed positionof the third segment 2218 shown in FIGS. 22-24 and the stowed positionof the third segment 2218 shown in FIG. 25 . The outer mold line 2236 ofthe third segment 2218 extends along the outer surface 2212 of thenacelle 2200 when the third segment 2218 is positioned in its stowedposition. As shown in FIG. 25 , the outer mold line 2236 of the thirdsegment 2218 is received in the recess 2210 of the nacelle 2200 when thethird segment 2218 is positioned in its stowed position. The outer moldline 2236 of the third segment 2218 extends outwardly (e.g., radiallyoutwardly) from the outer surface 2212 of the nacelle 2200 when thethird segment 2218 is positioned in its deployed position.

When the multi-segment chine 2202 of FIGS. 22-25 is positioned in thefirst configuration shown in FIG. 22 , the first segment 2214, thesecond segment 2216, and the third segment 2218 of the multi-segmentchine 2202 are positioned in their respective deployed positions and aresubstantially coplanar with one another. When the multi-segment chine2202 of FIGS. 22-25 is positioned in the second configuration shown inFIG. 23 , the first segment 2214 of the multi-segment chine 2202 ispositioned in its stowed position, the second segment 2216 and the thirdsegment 2218 of the multi-segment chine 2202 are positioned in theirrespective deployed positions, and the second segment 2216 and the thirdsegment 2218 of the multi-segment chine 2202 are substantially coplanarwith one another, but not with the first segment 2214 of themulti-segment chine 2202. When the multi-segment chine 2202 of FIGS.22-25 is positioned in the third configuration shown in FIG. 24 , thefirst segment 2214 and the second segment 2216 of the multi-segmentchine 2202 are positioned in their respective stowed positions, thethird segment 2218 of the multi-segment chine 2202 is positioned in itsdeployed position, and the first segment 2214 and the second segment2216 of the multi-segment chine 2202 are substantially coplanar with oneanother, but not with the third segment 2218 of the multi-segment chine2202. When the multi-segment chine 2202 of FIGS. 22-25 is positioned inthe fourth configuration shown in FIG. 25 , the first segment 2214, thesecond segment 2216, and the third segment 2218 of the multi-segmentchine 2202 are positioned in their respective stowed positions and aresubstantially coplanar with one another.

In the illustrated example of FIGS. 22-25 , the first segment 2214, thesecond segment 2216 and/or the third segment 2218 of the multi-segmentchine 2202 can be rotated in a controlled manner to any number ofintermediate positions between the respective deployed positions and therespective stowed positions described above. The controlled rotation(s)of the first segment 2214, the second segment 2216 and/or the thirdsegment 2218 of the multi-segment chine 2202 occur(s) via one or moreactuation mechanism(s) and one or more controller(s) of a control system(e.g., the actuation mechanism 3404 and the controller 3406 of thecontrol system 3400 of FIG. 34 ), as further described below.

The multi-segment chine 2202 of FIGS. 22-25 is configured (e.g., locatedon and/or oriented relative to the nacelle 2200 of FIGS. 22-25 ) togenerate a vortex in response to an airflow presented at themulti-segment chine 2202. In some examples, the vortex generated by themulti-segment chine 2202 favorably affects a boundary layer located onan upper surface of an aircraft wing to which the nacelle 2200 of FIGS.22-25 is coupled. Thus, the multi-segment chine 2202 provides a positiveaerodynamic impact in response to an airflow presented at themulti-segment chine 2202. The vortex generated by the multi-segmentchine 2202 of FIGS. 22-25 changes (e.g., changes its position and/or itsstrength) as the first segment 2214, the second segment 2216 and/or thethird segment 2218 of the multi-segment chine 2202 are respectivelymoved (e.g., rotated about the axis of rotation 2208) between the firstconfiguration shown in FIG. 22 , the second configuration shown in FIG.23 , the third configuration shown in FIG. 24 , and the fourthconfiguration shown in FIG. 25 .

For example, when the first segment 2214, the second segment 2216, andthe third segment 2218 of the multi-segment chine 2202 are positioned inthe first configuration shown in FIG. 22 , the multi-segment chine 2202is configured to generate a first vortex. When the first segment 2214,the second segment 2216, and the third segment 2218 of the multi-segmentchine 2202 are positioned in the second configuration shown in FIG. 23 ,the multi-segment chine 2202 is configured to generate a second vortexthat differs from the first vortex. When the first segment 2214, thesecond segment 2216, and the third segment 2218 of the multi-segmentchine 2202 are positioned in the third configuration shown in FIG. 24 ,the multi-segment chine 2202 is configured to generate a third vortexthat differs from the first vortex and also differs from the secondvortex. When the first segment 2214, the second segment 2216, and thethird segment 2218 of the multi-segment chine 2202 are positioned in thefourth configuration shown in FIG. 24 , the multi-segment chine 2202does not generate a vortex. In some examples, the first vortex has afirst associated vortex position, the second vortex has a secondassociated vortex position that differs from the first associated vortexposition, and the third vortex has a third associated vortex positionthat differs from each of the first and second associated vortexpositions. In some examples, the first vortex has a first associatedvortex strength, the second vortex has a second associated vortexstrength that differs from the first associated vortex strength, and thethird vortex has a third associated vortex strength that differs fromeach of the first and second associated vortex strengths.

FIG. 26 is a perspective view of an example nacelle 2600 having examplechines (e.g., a first example chine 2602 and a second example chine2604) positioned in a first example configuration. FIG. 27 is aperspective view of the nacelle 2600 of FIG. 26 having the chines ofFIG. 26 positioned in a second example configuration. The nacelle 2600of FIGS. 26 and 27 can be coupled to a wing of an aircraft (e.g., thefirst wing 104 of the aircraft 100 of FIGS. 1-3 ). The first chine 2602of the nacelle 2600 of FIGS. 26 and 27 can be controlled and/or adjustedby a control system of an aircraft (e.g., the control system 3400 ofFIG. 34 described below, which may be implemented in the aircraft 100 ofFIGS. 1-3 ).

The nacelle 2600 of FIGS. 26 and 27 includes an example central axis2606 and an example leading edge 2608. The first chine 2602 and/or thesecond chine 2604 of FIGS. 26 and 27 is/are oriented along an examplefore-aft direction 2610 relative to the nacelle 2600. In the illustratedexample of FIGS. 26 and 27 , the fore-aft direction 2610 is defined byan outer mold line of the first chine 2602 and/or an outer mold line ofthe second chine 2604, as further described below. In some examples, thefore-aft direction 2610 is substantially parallel to the central axis2606 of the nacelle 2600, with the central axis 2606 of the nacelle 2600being defined by a rotational axis of an engine housed by the nacelle2600. In other examples, the fore-aft direction 2610 can additionally oralternatively be substantially parallel to a longitudinal axis of afuselage of an aircraft (e.g., the longitudinal axis 116 of the fuselage102 of the aircraft 100 of FIGS. 1-3 ) that includes the nacelle 2600.In still other examples, the orientation of the fore-aft direction 2610can exceed the above-described substantially parallel relationship(s)relative to the central axis 2606 of the nacelle 2600 and/or thelongitudinal axis of the fuselage of the aircraft. The nacelle 2600 ofFIGS. 26 and 27 further includes an example outer circumference 2612.

The first chine 2602 (e.g., a spoiler chine) of FIGS. 26 and 27 includesan example leading edge 2614, an example trailing edge 2616 locatedopposite and/or rearward of the leading edge 2614 of the first chine2602, and an outer mold line 2618 defined by the leading edge 2614 andthe trailing edge 2616 of the first chine 2602. The first chine 2602 ofFIGS. 26 and 27 has a substantially planar shape (e.g., as defined bythe outer mold line 2618) that extends and/or is oriented along thefore-aft direction 2610. In some examples, the substantially planarshape of the first chine 2602 can be contoured to match a contour of therecess 2702 and/or a contour of a local area of the outer surface 2622of the nacelle 2600.

The first chine 2602 of FIGS. 26 and 27 is rotatably coupled to thenacelle 2600 at a first location about the outer circumference 2612 ofthe nacelle 2600, and is rotatable relative to the nacelle 2600 about anexample axis of rotation 2620. In the illustrated example of FIGS. 26and 27 , the axis of rotation 2620 of the first chine 2602 issubstantially parallel to the fore-aft direction 2610. In otherexamples, the axis of rotation 2620 can additionally or alternatively besubstantially parallel to the central axis 2606 of the nacelle 2600. Instill other examples, the orientation of the axis of rotation 2620 ofthe first chine 2602 can exceed the above-described substantiallyparallel relationship relative to the central axis 2606 of the nacelle2600. The nacelle 2600 of FIGS. 26 and 27 further includes an examplerecess 2702 formed in and/or extending into an example outer surface2622 of the nacelle 2600. The recess 2702 is sized, shaped and/orconfigured to receive the first chine 2602 of FIGS. 26 and 27 , asfurther described below.

The second chine 2604 (e.g., a fixed chine) of FIGS. 26 and 27 includesan example leading edge 2624, an example trailing edge 2626 locatedopposite and/or rearward of the leading edge 2624 of the second chine2604, and an outer mold line 2628 defined by the leading edge 2624 andthe trailing edge 2626 of the second chine 2604. The second chine 2604of FIGS. 26 and 27 has a substantially planar shape (e.g., as defined bythe outer mold line 2628) that extends and/or is oriented along thefore-aft direction 2610. The second chine 2604 of FIGS. 26 and 27 isfixedly coupled to the nacelle 2600 at a second location about the outercircumference 2612 of the nacelle 2600 that is circumferentially offsetfrom the first location about the outer circumference 2612 of thenacelle 2600 at which the first chine 2602 is coupled to the nacelle2600.

In the illustrated example of FIGS. 26 and 27 , the first location atwhich the first chine 2602 is coupled to the nacelle 2600 is below thesecond position at which the second chine 2604 is coupled to the nacelle2600. In other examples, the first location at which the first chine2602 is coupled to the nacelle 2600 can alternatively be above thesecond position at which the second chine 2604 is coupled to the nacelle2600. As shown in FIGS. 26 and 27 , the leading edge 2614 of the firstchine 2602 is spaced from the leading edge 2608 of the nacelle 2600 by afirst distance, and the leading edge 2624 of the second chine 2604 isspaced from the leading edge 2608 of the nacelle 2600 by a seconddistance less than the first distance. In other examples, the leadingedge 2624 of the second chine 2604 can alternatively be spaced from theleading edge 2608 of the nacelle 2600 by a second distance that isgreater than a first distance by which the leading edge 2614 of thefirst chine 2602 is spaced from the leading edge 2608 of the nacelle2600. In the illustrated example of FIGS. 26 and 27 , the first chine2602 and the second chine 2604 are respectively coupled to the nacelle2600 at locations that are inboard relative to the central axis 2606 ofthe nacelle 2600. In other examples, the first chine 2602 and the secondchine 2604 can alternatively be respectively coupled to the nacelle 2600at locations that are outboard relative to the central axis 2606 of thenacelle 2600.

The first configuration of the chines shown in FIG. 26 corresponds to astowed position of the first chine 2602 and a deployed position of thesecond chine 2604. The second configuration of the chines shown in FIG.27 corresponds to a deployed position of the first chine 2602 and adeployed position of the second chine 2604. The first chine 2602 ofFIGS. 26 and 27 is rotatable about the axis of rotation 2620 between thestowed position of the first chine 2602 shown in FIG. 26 and thedeployed position of the first chine 2602 shown in FIG. 27 . The outermold line 2618 of the first chine 2602 extends along the outer surface2622 of the nacelle 2600 when the first chine 2602 is positioned in itsstowed position. As shown in FIG. 26 , the outer mold line 2618 of thefirst chine 2602 is received in the recess 2702 of the nacelle 2600 whenthe first chine 2602 is positioned in its stowed position. The outermold line 2618 of the first chine 2602 extends outwardly (e.g., radiallyoutwardly) from the outer surface 2622 of the nacelle 2600 when thefirst chine 2602 is positioned in its deployed position.

In the illustrated example of FIGS. 26 and 27 , the first chine 2602 canbe moved (e.g., rotated about the axis of rotation 2620) in a controlledmanner to any number of intermediate positions between the firstposition (e.g., the stowed position) shown in FIG. 26 and the secondposition (e.g., the deployed position) shown in FIG. 27 . The controlledmovement (e.g., rotation) of the first chine 2602 occurs via anactuation mechanism and a controller of a control system (e.g., theactuation mechanism 3404 and the controller 3406 of the control system3400 of FIG. 34 ), as further described below.

The second chine 2604 of FIGS. 26 and 27 is configured (e.g., located onand/or oriented relative to the nacelle 2600 of FIGS. 26 and 27 ) togenerate a vortex in response to an airflow presented at the secondchine 2604. In some examples, the vortex generated by the second chine2604 favorably affects a boundary layer located on an upper surface ofan aircraft wing to which the nacelle 2600 of FIGS. 26 and 27 iscoupled. Thus, the second chine 2604 provides a positive aerodynamicimpact in response to an airflow presented at the second chine 2604. Avortex (e.g., a combined set of vortices) generated by the first chine2602 and the second chine 2604 of FIGS. 26 and 27 changes (e.g., changesits position and/or its strength) as the first chine 2602 of FIGS. 26and 27 is moved (e.g., rotated about the axis of rotation 2620) betweenthe first position (e.g., the stowed position) shown in FIG. 26 and thesecond position (e.g., the deployed position) shown in FIG. 27 .

For example, when the first chine 2602 and the second chine 2604 arepositioned in the first configuration shown in FIG. 26 , the secondchine 2604 generates a vortex, but the first chine 2602 does notgenerate a vortex. The first chine 2602 and the second chine 2604accordingly produce a first vortex (e.g., a first combined set ofvortices that includes the vortex generated by the second chine 2604,with no vortex being generated by the first chine 2602). When the firstchine 2602 and the second chine 2604 are positioned in the secondconfiguration shown in FIG. 27 , the first chine 2602 generates a vortexthat interacts (e.g., combines) with the vortex generated by the secondchine 2604 to produce a second vortex (e.g., a second combined set ofvortices that includes the vortex generated by the second chine 2604, aswell as the vortex generated by the first chine 2602) that differs fromthe first vortex. In some examples, positioning the first chine 2602 inthe deployed position shown in FIG. 27 causes the first chine 2602 toproduce a vortex that reduces, limits and/or spoils the vortex generatedby the second chine 2604, or that combines with the vortex generated bythe second chine 2604 to alter the effect it has on the wingaerodynamics.

FIG. 28 is a perspective view of an example nacelle 2800 having anexample chine 2802 positioned in a first example position. FIG. 29 is aperspective view of the nacelle 2800 of FIG. 28 having the chine 2802 ofFIG. 28 rotated to a second example position. FIG. 30 is a perspectiveview of the nacelle 2800 of FIGS. 28 and 29 having the chine 2802 ofFIGS. 28 and 29 rotated to a third example position. The nacelle 2800 ofFIGS. 28-30 can be coupled to a wing of an aircraft (e.g., the firstwing 104 of the aircraft 100 of FIGS. 1-3 ). The chine 2802 of thenacelle 2800 of FIGS. 28-30 can be controlled and/or adjusted by acontrol system of an aircraft (e.g., the control system 3400 of FIG. 34described below, which may be implemented in the aircraft 100 of FIGS.1-3 ).

The nacelle 2800 of FIGS. 28-30 includes an example central axis 2804and an example leading edge 2806. The central axis 2804 of the nacelle2800 approximately defines an example fore-aft direction 2808 of thenacelle 2800. In some examples, the fore-aft direction 2808 of thenacelle 2800 is substantially parallel to the central axis 2804 of thenacelle 2800, with the central axis 2804 of the nacelle 2800 beingdefined by a rotational axis of an engine housed by the nacelle 2800. Inother examples, the fore-aft direction 2808 of the nacelle 2800 canadditionally or alternatively be substantially parallel to alongitudinal axis of a fuselage of an aircraft (e.g., the longitudinalaxis 116 of the fuselage 102 of the aircraft 100 of FIGS. 1-3 ) thatincludes the nacelle 2800. In still other examples, the orientation ofthe fore-aft direction 2808 of nacelle 2800 can exceed theabove-described substantially parallel relationship(s) relative to thecentral axis 2804 of the nacelle 2800 and/or the longitudinal axis ofthe fuselage of the aircraft.

The chine 2802 of FIGS. 28-30 includes an example leading edge 2810, anexample trailing edge 2812 located opposite and/or rearward of theleading edge 2810 of the chine 2802, and an example outer mold line 2814defined by the leading edge 2810 and the trailing edge 2812 of the chine2802. The chine 2802 of FIGS. 28-30 has a substantially planar shape(e.g., as defined by the outer mold line 2814). In the illustratedexample of FIGS. 28-30 , the outer mold line 2814 of the chine 2802extends outwardly (e.g., radially outwardly) from an example outersurface 2820 of the nacelle 2800. The chine 2802 of FIGS. 28-30 isrotatably coupled to the nacelle 2800 via an example shaft 2816. Theshaft 2816 of FIGS. 28-30 defines an example axis of rotation 2818. Inthe illustrated example of FIGS. 28-30 , the axis of rotation 2818 issubstantially perpendicular to an example local area 2822 of the outersurface 2820 of the nacelle 2800. The chine 2802 of FIGS. 28-30 ismovable and/or adjustable relative to the nacelle 2800 of FIGS. 28-30 .More specifically, the chine 2802 of FIGS. 28-30 is rotatable relativeto the nacelle 2800 of FIGS. 28-30 about the axis of rotation 2818. Inthe illustrated example of FIGS. 28-30 , the chine 2802 is coupled tothe nacelle 2800 (e.g., via the shaft 2816) at a location that isinboard relative to the central axis 2804 of the nacelle 2800. In otherexamples, the chine 2802 can alternatively be coupled to the nacelle2800 at a location that is outboard relative to the central axis 2804 ofthe nacelle 2800.

In the illustrated example of FIGS. 28-30 , the chine 2802 is movable(e.g., rotatable about the axis of rotation 2818) to a first position(e.g., a neutral position) shown in FIG. 28 in which the chine 2802 isoriented along the fore-aft direction 2808 of the nacelle 2800. Thechine 2802 is movable (e.g., rotatable about the axis of rotation 2818)from the first position shown in FIG. 28 to either of a second position(e.g., an upward-pitched position) shown in FIG. 29 in which the leadingedge 2810 of the chine 2802 is oriented at an upward angle relative tothe position of the leading edge 2810 of the chine 2802 in the neutralposition shown in FIG. 28 , or a third position (e.g., adownward-pitched position) shown in FIG. 30 in which the leading edge2810 of the chine 2802 is oriented at a downward angle relative to theposition of the leading edge 2810 of the chine 2802 in the neutralposition shown in FIG. 28 .

The chine 2802 of FIGS. 28-30 can be moved (e.g., rotated about the axisof rotation 2818) in a controlled manner to any number of intermediatepositions between the second position shown in FIG. 29 and the thirdposition shown in FIG. 30 , including to the neutral position shown inFIG. 28 . The controlled movement (e.g., rotation) of the chine 2802occurs via an actuation mechanism and a controller of a control system(e.g., the actuation mechanism 3404 and the controller 3406 of thecontrol system 3400 of FIG. 34 ), as further described below.

The chine 2802 of FIGS. 28-30 is configured (e.g., located on and/ororiented relative to the nacelle 2800 of FIGS. 28-30 ) to generate avortex in response to an airflow presented at the chine 2802. In someexamples, the vortex generated by the chine 2802 favorably affects aboundary layer located on an upper surface of an aircraft wing to whichthe nacelle 2800 of FIGS. 28-30 is coupled. Thus, the chine 2802provides a positive aerodynamic impact in response to an airflowpresented at the chine 2802. The vortex generated by the chine 2802 ofFIGS. 28-30 changes (e.g., changes its position and/or its strength) asthe chine 2802 is moved (e.g., rotated about the axis of rotation 2818)between the first position (e.g., a neutral position) shown in FIG. 28 ,the second position (e.g., an upward-pitched position) shown in FIG. 29, and the third position (e.g., a downward-pitched position) shown inFIG. 30 .

For example, when the chine 2802 is positioned in the first positionshown in FIG. 28 , the chine 2802 is configured to generate a firstvortex. When the chine 2802 is positioned in the second position shownin FIG. 29 , the chine 2802 is configured to generate a second vortexthat differs from the first vortex. When the chine 2802 is positioned inthe third position shown in FIG. 30 , the chine 2802 is configured togenerate a third vortex that differs from the first vortex and alsodiffers from the second vortex. In some examples, the first vortex has afirst associated vortex position, the second vortex has a secondassociated vortex position that differs from the first associated vortexposition, and the third vortex has a third associated vortex positionthat differs from the first associated vortex position and also differsfrom the second associated vortex position. In some examples, the firstvortex has a first associated vortex strength, the second vortex has asecond associated vortex strength that differs from the first associatedvortex strength, and the third vortex has a third associated vortexstrength that differs from the first associated vortex strength and alsodiffers from the second associated vortex strength.

FIG. 31 is a perspective view of an example nacelle 3100 having anexample multi-segment chine 3102 positioned in a first exampleconfiguration. FIG. 32 is a perspective view of the nacelle 3100 of FIG.31 having the multi-segment chine 3102 of FIG. 31 positioned in a secondexample configuration. FIG. 33 is a perspective view of the nacelle 3100of FIGS. 31 and 32 having the multi-segment chine 3102 of FIGS. 31 and32 positioned in a third example configuration. The nacelle 3100 ofFIGS. 31-33 can be coupled to a wing of an aircraft (e.g., the firstwing 104 of the aircraft 100 of FIGS. 1-3 ). The multi-segment chine3102 of the nacelle 3100 of FIGS. 31-33 can be controlled and/oradjusted by a control system of an aircraft (e.g., the control system3400 of FIG. 34 described below, which may be implemented in theaircraft 100 of FIGS. 1-3 ).

The nacelle 3100 of FIGS. 31-33 includes an example central axis 3104and an example leading edge 3106. The central axis 3104 of the nacelle3100 approximately defines an example fore-aft direction 3108 of thenacelle 3100. In some examples, the fore-aft direction 3108 of thenacelle 3100 is substantially parallel to the central axis 3104 of thenacelle 3100, with the central axis 3104 of the nacelle 3100 beingdefined by a rotational axis of an engine housed by the nacelle 3100. Inother examples, the fore-aft direction 3108 of the nacelle 3100 canadditionally or alternatively be substantially parallel to alongitudinal axis of a fuselage of an aircraft (e.g., the longitudinalaxis 116 of the fuselage 102 of the aircraft 100 of FIGS. 1-3 ) thatincludes the nacelle 3100. In still other examples, the orientation ofthe fore-aft direction 3108 of nacelle 3100 can exceed theabove-described substantially parallel relationship(s) relative to thecentral axis 3104 of the nacelle 3100 and/or the longitudinal axis ofthe fuselage of the aircraft.

The multi-segment chine 3102 of FIGS. 31-33 includes an example firstsegment 3110 (e.g., a leading segment) and an example second segment3112 (e.g., a trailing segment). The first segment 3110 of themulti-segment chine 3102 of FIGS. 31-33 includes an example leading edge3114, an example trailing edge 3116 located opposite and/or rearward ofthe leading edge 3114 of the first segment 3110 of the multi-segmentchine 3102, and an example outer mold line 3118 defined by the leadingedge 3114 and the trailing edge 3116 of the first segment 3110 of themulti-segment chine 3102. The first segment 3110 of the multi-segmentchine 3102 of FIGS. 31-33 has a substantially planar shape (e.g., asdefined by the outer mold line 3118). In the illustrated example ofFIGS. 31-33 , the outer mold line 3118 of the first segment 3110 of themulti-segment chine 3102 extends outwardly (e.g., radially outwardly)from an example outer surface 3120 of the nacelle 3100.

The first segment 3110 of the multi-segment chine 3102 is coupled (e.g.,rigidly coupled) to the nacelle 3100. For example, the first segment3110 of the multi-segment chine 3102 can be fixedly coupled to a static(e.g., non-movable) structure located on and/or within the nacelle 3100.In the illustrated example of FIGS. 31-33 , the first segment 3110 ofthe multi-segment chine 3102 is oriented along (e.g., is substantiallyparallel to) the fore-aft direction 3108 of the nacelle 3100. In otherexamples, the orientation of the first segment 3110 of the multi-segmentchine 3102 can exceed the above-described substantially parallelrelationship relative to the fore-aft direction 3108 of the nacelle3100. In the illustrated example of FIGS. 31-33 , the first segment 3110of the multi-segment chine 3102 is coupled to the nacelle 3100 at alocation that is inboard relative to the central axis 3104 of thenacelle 3100. In other examples, the first segment 3110 of themulti-segment chine 3102 can alternatively be coupled to the nacelle3100 at a location that is outboard relative to the central axis 3104 ofthe nacelle 3100.

The second segment 3112 of the multi-segment chine 3102 of FIGS. 31-33includes an example leading edge 3122, an example trailing edge 3124located opposite and/or rearward of the leading edge 3122 of the secondsegment 3112 of the multi-segment chine 3102, and an example outer moldline 3126 defined by the leading edge 3122 and the trailing edge 3124 ofthe second segment 3112 of the multi-segment chine 3102. The secondsegment 3112 of the multi-segment chine 3102 of FIGS. 31-33 has asubstantially planar shape (e.g., as defined by the outer mold line3126). In the illustrated example of FIGS. 31-33 , the outer mold line3126 of the second segment 3112 of the multi-segment chine 3102 extendsoutwardly (e.g., radially outwardly) from the outer surface 3120 of thenacelle 3100.

The second segment 3112 of the multi-segment chine 3102 of FIGS. 31-33is rotatably coupled to the first segment 3110 of the multi-segmentchine 3102, and/or to the nacelle 3100, via an example hinge 3128. Inthe illustrated example of FIGS. 31-33 , the hinge 3128 defines anexample axis of rotation 3130 located at the trailing edge 3116 of thefirst segment 3110 of the multi-segment chine 3102 and at the leadingedge 3122 of the second segment 3112 of the multi-segment chine 3102. Inthe illustrated example of FIGS. 31-33 , the axis of rotation 3130 issubstantially perpendicular to an example local area 3132 of the outersurface 3120 of the nacelle 3100.

The second segment 3112 of the multi-segment chine 3102 of FIGS. 31-33is movable and/or adjustable relative to the first segment 3110 of themulti-segment chine 3102 of FIGS. 31-33 , and/or relative to the nacelle3100 of FIGS. 31-33 . More specifically, the second segment 3112 of themulti-segment chine 3102 of FIGS. 31-33 is rotatable relative to thefirst segment 3110 of the multi-segment chine 3102 of FIGS. 31-33 ,and/or relative to the nacelle 3100 of FIGS. 31-33 , about the axis ofrotation 3130. The second segment 3112 and/or the hinge 3128 of themulti-segment chine 3102 can be coupled (e.g., operatively coupled) toan actuation mechanism located within the nacelle 3100 to facilitatemovement (e.g., rotation) of the second segment 3112 of themulti-segment chine 3102 relative to the first segment 3110 of themulti-segment chine 3102, and/or relative to the nacelle 3100.

In the illustrated example of FIGS. 31-33 , the second segment 3112 ofthe multi-segment chine 3102 is movable (e.g., rotatable about the axisof rotation 3130) to a neutral position (e.g., as shown in FIG. 31 ) inwhich the second segment 3112 of the multi-segment chine 3102 issubstantially coplanar with the first segment 3110 of the multi-segmentchine 3102. The second segment 3112 of the multi-segment chine 3102 ismovable (e.g., rotatable about the axis of rotation 3130) from theneutral position shown in FIG. 31 to a first pitched position (e.g., asshown in FIG. 32 ) and/or to a second pitched position (e.g., as shownin FIG. 33 ). When the second segment 3112 of the multi-segment chine3102 is positioned in the first pitched position shown in FIG. 32 , thesecond segment 3112 is positioned at a first angle relative to the firstsegment 3110 of the multi-segment chine 3102. When the second segment3112 of the multi-segment chine 3102 is positioned in the second pitchedposition shown in FIG. 33 , the second segment 3112 is positioned at asecond angle relative to the first segment 3110 of the multi-segmentchine 3102 that is greater than the first angle.

The second segment 3112 of the multi-segment chine 3102 of FIGS. 31-33can be moved (e.g., rotated about the axis of rotation 3130) in acontrolled manner to any number of intermediate positions between theneutral position shown in FIG. 31 and the second pitched position shownin FIG. 33 , including to the first pitched position shown in FIG. 32 .Furthermore, although FIGS. 32 and 33 illustrate the trailing edge 3124of the second segment 3112 of the multi-segment chine 3102 beingdeflected in an upward direction, in other examples the trailing edge3124 of the second segment 3112 of the multi-segment chine 3102 canadditionally or alternatively be deflected in a downward directionopposite the upward direction. The controlled movement (e.g., rotation)of the second segment 3112 of the multi-segment chine 3102 occurs via anactuation mechanism and a controller of a control system (e.g., theactuation mechanism 3404 and the controller 3406 of the control system3400 of FIG. 34 ), as further described below.

The multi-segment chine 3102 of FIGS. 31-33 is configured (e.g., locatedon and/or oriented relative to the nacelle 3100 of FIGS. 31-33 ) togenerate a vortex in response to an airflow presented at themulti-segment chine 3102. In some examples, the vortex generated by themulti-segment chine 3102 favorably affects a boundary layer located onan upper surface of an aircraft wing to which the nacelle 3100 of FIGS.31-33 is coupled. Thus, the multi-segment chine 3102 provides a positiveaerodynamic impact in response to an airflow presented at themulti-segment chine 3102. The vortex generated by the multi-segmentchine 3102 of FIGS. 31-33 changes (e.g., changes its position and/or itsstrength) as the second segment 3112 of the multi-segment chine 3102 ismoved (e.g., rotated about the axis of rotation 3130) between theneutral position shown in FIG. 31 , the first pitched position shown inFIG. 32 , and the second pitched position shown in FIG. 32 .

For example, when the second segment 3112 of the multi-segment chine3102 is positioned in the neutral position shown in FIG. 31 , themulti-segment chine 3102 is configured to generate a first vortex. Whenthe second segment 3112 of the multi-segment chine 3102 is positioned inthe first pitched position shown in FIG. 32 , the multi-segment chine3102 is configured to generate a second vortex that differs from thefirst vortex. When the second segment 3112 of the multi-segment chine3102 is positioned in the second pitched position shown in FIG. 33 , themulti-segment chine 3102 is configured to generate a third vortex thatdiffers from the first vortex and also differs from the second vortex.In some examples, the first vortex has a first associated vortexposition, the second vortex has a second associated vortex position thatdiffers from the first associated vortex position, and the third vortexhas a third associated vortex position that differs from the firstassociated vortex position and also differs from the second associatedvortex position. In some examples, the first vortex has a firstassociated vortex strength, the second vortex has a second associatedvortex strength that differs from the first associated vortex strength,and the third vortex has a third associated vortex strength that differsfrom the first associated vortex strength and also differs from thesecond associated vortex strength.

FIG. 34 is a block diagram of an example control system 3400 configuredto control the movement of an adjustable chine of a nacelle. The controlsystem 3400 of FIG. 34 includes one or more example chine(s) 3402, oneor more example actuation mechanism(s) 3404, an example controller 3406,one or more example angle of attack sensor(s) 3408, one or more exampleleading edge device sensor(s) 3410, and one or more example trailingedge device sensor(s) 3412. The control system 3400 of FIG. 34 canfurther include one or more other sensor(s) 3414 including, for example,one or more attitude sensor(s), one or more altitude sensor(s), one ormore airspeed sensor(s), one or more Mach number sensor(s), etc. In theillustrated example of FIG. 34 , the actuation mechanism(s) 3404 is/areoperatively coupled to the chine(s) 3402. For example, a first one ofthe actuation mechanism(s) 3404 can be operatively coupled to a firstone of the chine(s) 3402, and a second one of the actuation mechanism(s)3404 can be operatively coupled to a second one of the chine(s) 3402.The controller 3406 is operatively coupled to the actuation mechanism(s)3404. For example, the controller 3406 can be operatively coupled to afirst one and a second one of the actuation mechanism(s) 3404. The angleof attack sensor(s) 3408, the leading edge device sensor(s) 3410, thetrailing edge device sensor(s) 3412, and the other sensor(s) 3414 arerespectively operatively coupled to the controller 3406.

The control system 3400 of FIG. 34 can be implemented in the aircraft100 of FIGS. 1-3 . For example, the chine(s) 3402 of the control system3400 can be implemented by and/or as the first chine 112 coupled to thefirst nacelle 108 of the aircraft 100 of FIGS. 1-3 , and/or by thesecond chine 114 coupled to the second nacelle 110 of the aircraft 100of FIGS. 1-3 . The actuation mechanism(s) 3404 of the control system3400 can be located (e.g., partially or fully located) within and/or onthe first nacelle 108 and/or the second nacelle 110 of the aircraft 100of FIGS. 1-3 , and may include portions and/or components located withinand/or on the first wing 104, the second wing 106, and/or the fuselage102 of the aircraft 100 of FIGS. 1-3 . The controller 3406 of thecontrol system 3400 can be located within and/or on any of the firstnacelle 108, the second nacelle 110, the first wing 104, the second wing106, and/or the fuselage 102 of the aircraft 100 of FIGS. 1-3 . Theangle of attack sensor(s) 3408 of the control system 3400 can be locatedwithin and/or on any of the first nacelle 108, the second nacelle 110,the first wing 104, the second wing 106, and/or the fuselage 102 of theaircraft 100 of FIGS. 1-3 . The leading edge device sensor(s) 3410 ofthe control system 3400 can be located within and/or on one or more ofthe leading edge device(s) 122 of the first wing 104 and/or one or moreof the leading edge device(s) 130 of the second wing 106 of the aircraft100 of FIGS. 1-3 , within and/or on the first wing 104 and/or the secondwing 106 of the aircraft 100, or within and/or on the fuselage 102 ofthe aircraft 100. The trailing edge device sensor(s) 3412 of the controlsystem 3400 can be located within and/or on one or more of the trailingedge device(s) 124 of the first wing 104 and/or one or more of thetrailing edge device(s) 132 of the second wing 106 of the aircraft 100of FIGS. 1-3 , within and/or on the first wing 104 and/or the secondwing 106 of the aircraft 100, or within and/or on the fuselage 102 ofthe aircraft 100. The other sensor(s) 3414 of the control system 3400can be located within and/or on any of the first nacelle 108, the secondnacelle 110, the first wing 104, the second wing 106, and/or thefuselage 102 of the aircraft 100 of FIGS. 1-3 .

The chine(s) 3402 of the control system 3400 of FIG. 34 can beimplemented by and/or as any of the example chines described above inconnection with FIGS. 4-30 and, more specifically, by any movable and/oradjustable components of such example chines. For example, the chine(s)3402 of FIG. 34 can be implemented by and/or as the chine 402 of FIGS. 4and 5 . The chine(s) 3402 of FIG. 34 can alternatively be implemented byand/or as the multi-segment chine 602 of FIGS. 6-10 and, morespecifically, by and/or as the first segment 618 and/or the secondsegment 620 of the multi-segment chine 602 of FIGS. 6-10 . The chine(s)3402 of FIG. 34 can alternatively be implemented by and/or as the chine1102 of FIGS. 11-13 . The chine(s) 3402 of FIG. 34 can alternatively beimplemented by and/or as the chine 1402 of FIGS. 14-16 . The chine(s)3402 of FIG. 34 can alternatively be implemented by and/or as themulti-segment chine 1702 of FIGS. 17 and 18 and/or, more specifically,by and/or as the first segment 1718 of the multi-segment chine 1702 ofFIGS. 17 and 18 . The chine(s) 3402 of FIG. 34 can alternatively beimplemented by and/or as the multi-segment chine 1902 of FIGS. 19-21and/or, more specifically, by and/or as the first segment 1918 of themulti-segment chine 1902 of FIGS. 19-21 . The chine(s) 3402 of FIG. 34can alternatively be implemented by and/or as the multi-segment chine2202 of FIGS. 22-25 and/or, more specifically, by and/or as the firstsegment 2214, the second segment 2216, and/or the third segment 2218 ofthe multi-segment chine 2202 of FIGS. 22-25 . The chine(s) 3402 of FIG.34 can alternatively be implemented by and/or as the first chine 2602 ofFIGS. 26 and 27 . The chine(s) 3402 of FIG. 34 can alternatively beimplemented by and/or as the chine 2802 of FIGS. 28-30 . The chine(s)3402 of FIG. 34 can alternatively be implemented by and/or as themulti-segment chine 3102 of FIGS. 31-33 and/or, more specifically, byand/or as the second segment 3112 of the multi-segment chine 3102 ofFIGS. 31-33 .

The actuation mechanism(s) 3404 of the control system 3400 of FIG. 34can be implemented by and/or as any type of actuation mechanism that iscapable of being configured to fit partially and/or fully within or on anacelle to which the chine(s) 3402 of FIG. 34 is/are coupled, and whichis capable of being configured to move (e.g., translate and/or rotate)all or part of the chine(s) 3402 of FIG. 34 over a desired and/orspecified range of positions. In some examples, the actuationmechanism(s) 3404 of FIG. 34 can be implemented by and/or as anelectro-mechanical actuation system that includes one or more electroniccomponent(s). In other examples, the actuation mechanism(s) 3404 of FIG.34 can be implemented by and/or as a hydro-mechanical actuation systemthat includes one or more hydraulic component(s). In still otherexamples, the actuation mechanism(s) 3404 of FIG. 34 can be implementedby and/or as a pneumatic-mechanical actuation system that includes oneor more pneumatic component(s). The actuation mechanism(s) 3404 of FIG.34 can include any number of mechanical components including, forexample, any number of motors, valves, latches, pistons, rods, shafts,links, pulleys, chains, belts, hinges, pins, biasing elements, shapememory alloys, etc.

The controller 3406 of the control system 3400 of FIG. 34 can beimplemented by and/or as any type of hardware element capable of beingconfigured to control the actuation mechanism(s) 3404 of the controlsystem 3400 of FIG. 34 , and/or capable of being configured to receiveand/or process data sensed, measured and/or detected by the angle ofattack sensor(s) 3408, the leading edge device sensor(s) 3410, thetrailing edge device sensor(s) 3412, and/or the other sensor(s) 3414 ofthe control system 3400 of FIG. 34 . The controller 3406 of FIG. 34 canbe implemented by one or more controller(s), processor(s),microcontroller(s), microprocessor(s), and/or circuit(s).

The angle of attack sensor(s) 3408 of the control system 3400 of FIG. 34is/are configured to sense, measure and/or detect the angle of attack ofan aircraft wing (e.g., the angle between the chord line of the aircraftwing and the relative direction of airflow against the aircraft wing),or the angle of attack relative to a fuselage of the aircraft 100 (e.g.,the angle between the fuselage centerline and the relative direction ofairflow against the fuselage). The leading edge device sensor(s) 3410 ofthe control system 3400 of FIG. 34 is/are configured to sense, measureand/or detect the position and/or angle of one or more leading edgedevice(s) of an aircraft wing (e.g., the position and/or angle of theleading edge device(s) relative to a reference location and/ororientation of the aircraft wing). The trailing edge device sensor(s)3412 of the control system 3400 of FIG. 34 is/are configured to sense,measure and/or detect the position and/or angle of one or more trailingedge device(s) of an aircraft wing (e.g., the position and/or angle ofthe trailing edge device(s) relative to a reference location and/ororientation of the aircraft wing). The other sensor(s) 3414 of thecontrol system 3400 of FIG. 34 is/are configured to sense, measureand/or detect one or more other parameter(s) associated with theaircraft including, for example, an attitude of the aircraft, analtitude of the aircraft, an airspeed of the aircraft, a Mach number ofthe aircraft, etc.

The chine(s) 3402 of the control system 3400 of FIG. 34 , and/or one ormore segment(s) of the chine(s) 3402 of the control system 3400 of FIG.34 , can be moved (e.g., translated and/or rotated, depending upon theimplementation of the chine(s) 3402) in a controlled manner to anynumber of positions over a possible range of positions of the chine(s)3402. The controlled movement (e.g., translation and/or rotation) of thechine(s) 3402 and/or the segment(s) of the chine(s) 3402 occurs via theactuation mechanism(s) 3404 of the control system 3400 of FIG. 34 , withthe actuation mechanism(s) 3404 being managed and/or controlled via thecontroller 3406 of the control system 3400 of FIG. 34 . The controller3406 of FIG. 34 generates and/or transmits one or more command(s) thatcause(s) the actuation mechanism(s) 3404 of FIG. 34 to move (e.g.,translate and/or rotate) the chine(s) 3402 and/or the segment(s) of thechine(s) 3402 of FIG. 34 to one or more position(s) (e.g., a forwardposition, a rearward position, an upward position, a downward position,a stowed position, a deployed position, an upward-pitched position, adownward-pitched position, any number of intermediate positions over apossible range of positions, etc.) specified by, indicated by, and/orderived from the command(s).

In some examples, the controller 3406 of FIG. 34 is configured togenerate a command that causes the actuation mechanism(s) 3404 of FIG.34 to move the chine(s) 3402 and/or the segment(s) of the chine(s) 3402of FIG. 34 to a specified position in response to the controller 3406determining and/or detecting that a threshold parameter associated withan angle of attack has been sensed, measured and/or detected by theangle of attack sensor 3408 of FIG. 34 . In some examples, thecontroller 3406 of FIG. 34 is configured to generate a command thatcauses the actuation mechanism(s) 3404 of FIG. 34 to move the chine(s)3402 and/or the segment(s) of the chine(s) 3402 of FIG. 34 to aspecified position in response to the controller 3406 determining and/ordetecting that a threshold parameter associated with a position and/oran angle of one or more leading edge device(s) has been sensed, measuredand/or detected by the leading edge device sensor(s) 3410 of FIG. 34 .In some examples, the controller 3406 of FIG. 34 is configured togenerate a command that causes the actuation mechanism(s) 3404 of FIG.34 to move the chine(s) 3402 and/or the segment(s) of the chine(s) 3402of FIG. 34 to a specified position in response to the controller 3406determining and/or detecting that a threshold parameter associated witha position and/or an angle of one or more trailing edge device(s) hasbeen sensed, measured and/or detected by the trailing edge devicesensor(s) 3412 of FIG. 34 . In some examples, the controller 3406 ofFIG. 34 is configured to generate a command that causes the actuationmechanism(s) 3404 of FIG. 34 to move the chine(s) 3402 of FIG. 34 to aspecified position in response to the controller 3406 determining and/ordetecting that one or more threshold parameter(s) associated with anattitude of the aircraft, an altitude of the aircraft, an airspeed ofthe aircraft, a Mach number of the aircraft, etc. has/have been sensed,measured and/or detected by one or more of the other sensor(s) 3414 ofFIG. 34 .

From the foregoing, it will be appreciated that the above-disclosedaircraft nacelles having adjustable chines provide advantages over knownchine implementations. For example, known chine implementations lack anability to actively adjust and/or tune (e.g., granularly adjust and/ortune) the position of a vortex generated by the chine during flight, andfurther provide only near-binary control (e.g., on or off) of thestrength of the generated vortex during flight. Unlike the knownsolutions and/or known chine implementations described above, aircraftnacelles having adjustable chines disclosed herein advantageouslyprovide the ability to actively adjust and/or tune (e.g., granularlyadjust and/or tune) the position and/or the strength of a vortexgenerated by the chine during flight, thereby improving near-stall andpost-stall pitch control of the aircraft and increasing the maximumcoefficient of lift associated with the wings of the aircraft.

In some examples, an apparatus is disclosed. In some disclosed examples,the apparatus comprises a chine coupled to a nacelle. In some disclosedexamples, the chine is oriented along a fore-aft direction. In somedisclosed examples, the chine is translatable relative to the nacellealong the fore-aft direction.

In some disclosed examples, the fore-aft direction is defined by anouter mold line of the chine.

In some disclosed examples, the fore-aft direction is substantiallyparallel to a central axis of the nacelle.

In some disclosed examples, the chine is translatable along the fore-aftdirection between a first position in which a leading edge of the chineis spaced from a leading edge of the nacelle by a first distance, and asecond position in which the leading edge of the chine is spaced fromthe leading edge of the nacelle by a second distance greater than thefirst distance.

In some disclosed examples, the chine is positioned within a slot formedin an outer surface of the nacelle. In some disclosed examples, the slotis oriented along the fore-aft direction. In some disclosed examples,the chine is translatable within the slot between the first position andthe second position.

In some disclosed examples, the first position is a deployed positionand the second position is a stowed position.

In some disclosed examples, a portion of the chine extends outwardlyfrom an outer surface of the nacelle when the chine is in the deployedposition, and the portion of the chine is retracted inwardly from theouter surface of the nacelle when the chine is in the stowed position.

In some disclosed examples, the chine is configured to generate a firstvortex when the chine is in the first position. In some disclosedexamples, the chine is further configured to generate a second vortexwhen the chine is in the second position. In some disclosed examples,the second vortex differs from the first vortex.

In some disclosed examples, the apparatus further comprises an actuationmechanism operatively coupled to the chine. In some disclosed examples,the actuation mechanism is configured to translate the chine along thefore-aft direction. In some disclosed examples, the apparatus furthercomprises a controller operatively coupled to the actuation mechanism.In some disclosed examples, the controller is configured to control theactuation mechanism.

In some disclosed examples, the controller is configured to command theactuation mechanism to translate the chine in response to the controllerdetecting at least one of a first threshold parameter associated with anangle of attack of an aircraft to which the nacelle is coupled, a secondthreshold parameter associated with a leading edge device of a wing ofthe aircraft, a third threshold parameter associated with a trailingedge device of the wing, a fourth threshold parameter associated with anattitude of the aircraft, a fifth threshold parameter associated with analtitude of the aircraft, a sixth threshold parameter associated with anairspeed of the aircraft, or a seventh threshold parameter associatedwith a Mach number of the aircraft.

In some examples, a method is disclosed. In some disclosed examples, themethod comprises translating a chine coupled to a nacelle. In somedisclosed examples, the chine is oriented along a fore-aft direction. Insome disclosed examples, the chine is translatable relative to thenacelle along the fore-aft direction.

In some disclosed examples, the fore-aft direction is defined by anouter mold line of the chine.

In some disclosed examples, the fore-aft direction is substantiallyparallel to a central axis of the nacelle.

In some disclosed examples, translating the chine includes translatingthe chine along the fore-aft direction between a first position in whicha leading edge of the chine is spaced from a leading edge of the nacelleby a first distance, and a second position in which the leading edge ofthe chine is spaced from the leading edge of the nacelle by a seconddistance greater than the first distance.

In some disclosed examples, the chine is positioned within a slot formedin an outer surface of the nacelle. In some disclosed examples, the slotis oriented along the fore-aft direction. In some disclosed examples,the chine is translatable within the slot between the first position andthe second position.

In some disclosed examples, the first position is a deployed positionand the second position is a stowed position.

In some disclosed examples, a portion of the chine extends outwardlyfrom an outer surface of the nacelle when the chine is in the deployedposition, and the portion of the chine is retracted inwardly from theouter surface of the nacelle when the chine is in the stowed position.

In some disclosed examples, the method further comprises generating afirst vortex via the chine when the chine is in the first position. Insome disclosed examples, the method further comprises generating asecond vortex via the chine when the chine is in the second position. Insome disclosed examples, the second vortex differs from the firstvortex.

In some disclosed examples, the method further comprises controlling anactuation mechanism via a controller operatively coupled to theactuation mechanism. In some disclosed examples, the actuation mechanismis operatively coupled to the chine. In some disclosed examples, theactuation mechanism is configured to translate the chine along thefore-aft direction.

In some disclosed examples, controlling the actuation mechanism includescommanding the actuation mechanism, via the controller, to translate thechine in response to the controller detecting at least one of a firstthreshold parameter associated with an angle of attack of an aircraft towhich the nacelle is coupled, a second threshold parameter associatedwith a leading edge device of a wing of the aircraft, a third thresholdparameter associated with a trailing edge device of the wing, a fourththreshold parameter associated with an attitude of the aircraft, a fifththreshold parameter associated with an altitude of the aircraft, a sixththreshold parameter associated with an airspeed of the aircraft, or aseventh threshold parameter associated with a Mach number of theaircraft.

Although certain example methods, apparatus and articles of manufacturehave been disclosed herein, the scope of coverage of this patent is notlimited thereto. On the contrary, this patent covers all methods,apparatus and articles of manufacture fairly falling within the scope ofthe claims of this patent.

What is claimed is:
 1. An apparatus, comprising: a nacelle of anaircraft engine, the nacelle including an outer surface and a slotformed in the outer surface, the slot oriented along a fore-aftdirection of the nacelle, the slot including a front end and a rear endlocated opposite the front end; and a chine located on the nacelle, thechine including an outer mold line having a leading edge and a trailingedge located opposite the leading edge, the chine translatable withinthe slot along the fore-aft direction between a forward position and arearward position, the outer mold line extending radially outward fromthe outer surface when the chine is in the forward position, wherein theleading edge is adjacent the front end when the chine is in the forwardposition and spaced rearward of the front end when the chine is in therearward position, and wherein the trailing edge is spaced forward ofthe rear end when the chine is in the forward position and adjacent therear end when the chine is in the rearward position, wherein the forwardposition is a deployed position of the chine and the rearward positionis a stowed position of the chine, wherein a portion of the chineextends outwardly from the outer surface of the nacelle when the chineis in the deployed position, and the portion of the chine is retractedinwardlyfrom the outer surface of the nacelle when the chine is in thestowed position.
 2. The apparatus of claim 1, wherein the fore-aftdirection is substantially parallel to a central axis of the nacelle. 3.The apparatus of claim 1, wherein, in response to an airflow presentedat the chine, the chine is configured to: generate a first vortex whenthe chine is in the forward position; and generate a second vortex whenthe chine is in the rearward position, the second vortex differing fromthe first vortex.
 4. The apparatus of claim 1, further comprising: anactuation mechanism operatively coupled to the chine, the actuationmechanism configured to translate the chine within the slot along thefore-aft direction; and a controller operatively coupled to theactuation mechanism, the controller configured to control the actuationmechanism.
 5. The apparatus of claim 4, wherein the controller isconfigured to command the actuation mechanism to translate the chinewithin the slot in response to the controller detecting at least one ofa first threshold parameter associated with an angle of attack of anaircraft to which the nacelle is coupled, a second threshold parameterassociated with a leading edge device of a wing of the aircraft, a thirdthreshold parameter associated with a trailing edge device of the wing,a fourth threshold parameter associated with an attitude of theaircraft, a fifth threshold parameter associated with an altitude of theaircraft, a sixth threshold parameter associated with an airspeed of theaircraft, or a seventh threshold parameter associated with a Mach numberof the aircraft.
 6. The apparatus of claim 1, wherein the outer moldline of the chine extends radially outward from the outer surface whenthe chine is in the rearward position.
 7. The apparatus of claim 1,further comprising a wing, wherein the nacelle is coupled to the wingvia a pylon extending downward from the wing.
 8. The apparatus of claim7, wherein a leading edge of the nacelle and the leading edge of thechine are located forward of and below a leading edge of the wing whenthe chine is in the forward position.
 9. The apparatus of claim 1,wherein the outer mold line of the chine tapers toward the outer surfaceof the nacelle from the trailing edge of the chine toward the leadingedge of the chine.
 10. The apparatus of claim 1, wherein the chine has aplanar shape defined by the outer mold line.
 11. The apparatus of claim1, wherein the chine is located on the nacelle inboard of a central axisof the nacelle.
 12. A method, comprising: translating a chine located ona nacelle of an aircraft engine, the nacelle including an outer surfaceand a slot formed in the outer surface, the slot oriented along afore-aft direction of the nacelle, the slot including a front end and arear end located opposite the front end, the chine including an outermold line having a leading edge and a trailing edge located opposite theleading edge, the chine translatable within the slot along the fore-aftdirection between a forward position and a rearward position, the outermold line extending radially outward from the outer surface when thechine is in the forward position, wherein the leading edge is adjacentthe front end when the chine is in the forward position and spacedrearward of the front end when the chine is in the rearward position,and wherein the trailing edge is spaced forward of the rear end when thechine is in the forward position and adjacent the rear end when thechine is in the rearward position, wherein the forward position is adeployed position of the chine and the rearward position is a stowedposition of the chine, wherein a portion of the chine extends outwardlyfrom the outer surface of the nacelle when the chine is in the deployedposition, and the portion of the chine is retracted inwardlyfrom theouter surface of the nacelle when the chine is in the stowed position.13. The method of claim 12, wherein the fore-aft direction issubstantially parallel to a central axis of the nacelle.
 14. The methodof claim 12, further comprising, in response to an airflow presented atthe chine: generating a first vortex via the chine when the chine is inthe forward position; and generating a second vortex via the chine whenthe chine is in the rearward position, the second vortex differing fromthe first vortex.
 15. The method of claim 12, further comprising:controlling an actuation mechanism via a controller operatively coupledto the actuation mechanism, the actuation mechanism operatively coupledto the chine, the actuation mechanism configured to translate the chinewithin the slot along the fore-aft direction.
 16. The method of claim15, wherein controlling the actuation mechanism includes commanding theactuation mechanism, via the controller, to translate the chine withinthe slot in response to the controller detecting at least one of a firstthreshold parameter associated with an angle of attack of an aircraft towhich the nacelle is coupled, a second threshold parameter associatedwith a leading edge device of a wing of the aircraft, a third thresholdparameter associated with a trailing edge device of the wing, a fourththreshold parameter associated with an attitude of the aircraft, a fifththreshold parameter associated with an altitude of the aircraft, a sixththreshold parameter associated with an airspeed of the aircraft, or aseventh threshold parameter associated with a Mach number of theaircraft.